Canard fighters generally configured with wing canard-deltas and would generate
an airflow phenomenon producing vortex cores and lifts. The lift distribution would
stall at a high angle of attack (AoA). This study investigated the vortex dynamic of
wing canard delta configurations of the Saab JAS Gripen C-like model which create
different wing planform than other fighters. The slotted leading edge of the Gripen
would develop a strong vortex core on the outer wing, on the same direction with the
spin of wing vortex; the outer core would drag the inner vortex core and strengthened.
Consequently, the vortex core streamlined in a leading edge of the wing would begin
to detach, resulting rolled-up vortices in the wing leading edge followed by a solid
laminar stream which tends to curl out. The trailing edge of the wing tended to
laminarize backward. The result would be a negative surface pressure on the leading
edge above the canard and on the wing which causes more negative surface pressures.
An increase in AoA will generate a closer vortex breakdown location to the wing
leading edge. The location was calculated as the ratio of the axial velocity
The International Journal of Engineering and Science (IJES)theijes
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
IRJET- Particle Swarm Intelligence based Dynamics Economic Dispatch with Dail...IRJET Journal
This document presents a structural and modal analysis of the wing of a subsonic aircraft using ANSYS Workbench. The study analyzes the wing structure made of two materials, aluminum alloy and titanium alloy, under a pressure load of 500 Pa to determine which is best suited. A 3D model of the wing is created based on the NACA 4412 airfoil dimensions and meshed. Boundary conditions fixing one end and applying pressure are applied. For each material, the total deformation, equivalent stress, maximum principle stress, and equivalent strain are determined from the static structural analysis and compared to select the best material for withstanding the loads in wing design.
Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)Designage Solutions
Next part of "A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)" with case studies.
Find previous presentation here- http://www.slideshare.net/HarshadaGurav/a-review-of-flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
This document summarizes a computational fluid dynamics (CFD) study comparing the aerodynamic performance of a bio-inspired corrugated dragonfly wing aerofoil to conventional flat plate and NACA airfoils. CFD simulations were conducted at Reynolds numbers of 20,000-100,000 and angles of attack from 0-25 degrees. Results showed that the corrugated aerofoil had improved aerodynamic performance over the other airfoils, with a higher stall angle and increased lift. This is due to the corrugations reducing flow separation. The corrugated aerofoil design could potentially be incorporated into micro air vehicles (MAVs) to enhance their aerodynamic performance.
This study analyzed the aerodynamic characteristics of different cross-sectional sections along the wings of a dragonfly through computational fluid dynamics simulations. The wing sections had irregular corrugations that varied along the length of the wing. The results found that different sections had different aerodynamic lift, drag, glide ratio, glide angle, and minimum sinking rate due to their unique geometries and leading edge orientations. Section A7 was found to have the best aerodynamic performance metrics, making it well-optimized for technical applications like micro-air vehicles. The corrugated and varying geometry of dragonfly wings contributes significantly to their high lift generation and efficient flight.
International Journal of Engineering Research and Development (IJERD)IJERD Editor
journal publishing, how to publish research paper, Call For research paper, international journal, publishing a paper, IJERD, journal of science and technology, how to get a research paper published, publishing a paper, publishing of journal, publishing of research paper, reserach and review articles, IJERD Journal, How to publish your research paper, publish research paper, open access engineering journal, Engineering journal, Mathemetics journal, Physics journal, Chemistry journal, Computer Engineering, Computer Science journal, how to submit your paper, peer reviw journal, indexed journal, reserach and review articles, engineering journal, www.ijerd.com, research journals,
yahoo journals, bing journals, International Journal of Engineering Research and Development, google journals, hard copy of journal
Design and Analysis Nose Landing Gear SupportIJSRD
Nose landing gear support bracket is one of the main parts in the nose landing gear assembly, whose function is to maintain the stability of the landing gear during the movements. This work is focused on the FEA analysis of support bracket by varying the stress concentration area, The objective of this work is to determine the static and modal analysis of support bracket with different stress concentration areas, then analysis is done using ANSYS WORKBENCH, These results could provide some useful suggestions for design and improvement for the better component
The International Journal of Engineering and Science (IJES)theijes
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
IRJET- Particle Swarm Intelligence based Dynamics Economic Dispatch with Dail...IRJET Journal
This document presents a structural and modal analysis of the wing of a subsonic aircraft using ANSYS Workbench. The study analyzes the wing structure made of two materials, aluminum alloy and titanium alloy, under a pressure load of 500 Pa to determine which is best suited. A 3D model of the wing is created based on the NACA 4412 airfoil dimensions and meshed. Boundary conditions fixing one end and applying pressure are applied. For each material, the total deformation, equivalent stress, maximum principle stress, and equivalent strain are determined from the static structural analysis and compared to select the best material for withstanding the loads in wing design.
Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)Designage Solutions
Next part of "A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)" with case studies.
Find previous presentation here- http://www.slideshare.net/HarshadaGurav/a-review-of-flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
This document summarizes a computational fluid dynamics (CFD) study comparing the aerodynamic performance of a bio-inspired corrugated dragonfly wing aerofoil to conventional flat plate and NACA airfoils. CFD simulations were conducted at Reynolds numbers of 20,000-100,000 and angles of attack from 0-25 degrees. Results showed that the corrugated aerofoil had improved aerodynamic performance over the other airfoils, with a higher stall angle and increased lift. This is due to the corrugations reducing flow separation. The corrugated aerofoil design could potentially be incorporated into micro air vehicles (MAVs) to enhance their aerodynamic performance.
This study analyzed the aerodynamic characteristics of different cross-sectional sections along the wings of a dragonfly through computational fluid dynamics simulations. The wing sections had irregular corrugations that varied along the length of the wing. The results found that different sections had different aerodynamic lift, drag, glide ratio, glide angle, and minimum sinking rate due to their unique geometries and leading edge orientations. Section A7 was found to have the best aerodynamic performance metrics, making it well-optimized for technical applications like micro-air vehicles. The corrugated and varying geometry of dragonfly wings contributes significantly to their high lift generation and efficient flight.
International Journal of Engineering Research and Development (IJERD)IJERD Editor
journal publishing, how to publish research paper, Call For research paper, international journal, publishing a paper, IJERD, journal of science and technology, how to get a research paper published, publishing a paper, publishing of journal, publishing of research paper, reserach and review articles, IJERD Journal, How to publish your research paper, publish research paper, open access engineering journal, Engineering journal, Mathemetics journal, Physics journal, Chemistry journal, Computer Engineering, Computer Science journal, how to submit your paper, peer reviw journal, indexed journal, reserach and review articles, engineering journal, www.ijerd.com, research journals,
yahoo journals, bing journals, International Journal of Engineering Research and Development, google journals, hard copy of journal
Design and Analysis Nose Landing Gear SupportIJSRD
Nose landing gear support bracket is one of the main parts in the nose landing gear assembly, whose function is to maintain the stability of the landing gear during the movements. This work is focused on the FEA analysis of support bracket by varying the stress concentration area, The objective of this work is to determine the static and modal analysis of support bracket with different stress concentration areas, then analysis is done using ANSYS WORKBENCH, These results could provide some useful suggestions for design and improvement for the better component
This document analyzes the aerodynamic performance of blended winglets on aircraft wings through computational fluid dynamics modeling. It finds that winglets can increase the lift to drag ratio of wings by 6-15% compared to wings without winglets. The maximum efficiency occurs at a winglet cant angle of 45 degrees and an angle of attack of 4 degrees. CFD simulations are validated against experimental data and show good agreement on lift coefficient values. Winglets improve efficiency by reducing wingtip vortices and increasing effective aspect ratio without adding structural weight.
Fatigue life estimation of rear fuselage structure of an aircrafteSAT Journals
This document summarizes a study on estimating the fatigue life of the rear fuselage structure of an aircraft. The researchers created a finite element model of the rear fuselage structure in CATIA and analyzed it in MSC.PATRAN and MSC.NASTRAN to identify high stress regions. They found the maximum stress locations were at cut-out corners and rivet holes in the skin. A local model with finer meshing around the cargo door cut-out was also analyzed. Fatigue life was then estimated using Miner's rule and an S-N curve, accounting for factors like surface roughness and reliability. Damage was accumulated over the expected load cycles to predict fatigue life until crack initiation.
Abstract Joined wing layout UAVs feature multiple advantages compared to the rest of UAVs. Their best advantage is the maneuverability. The report contains the analysis of the applicable UAV maneuvers and their application in various flight missions. Keywords: UAV, Joined Wing, Maneuverability
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology
The document discusses design modifications and enhancements to the adaptability of mooring structures for medium-sized aerostats. It proposes three main modifications:
1) Mounting a bearing at the top of the mooring tower to eliminate twisting moments and reduce stresses.
2) Making the air bag frame adjustable to provide constant cushioned support to the balloon and keep it horizontal.
3) Fastening length pieces to allow the same structure to moor balloons of different sizes. Finite element analysis demonstrates that the modifications significantly reduce stresses on the structure.
Stress analysis and fatigue life prediction of wing fuselage lug joint attac...eSAT Publishing House
This document summarizes a study that performed stress analysis and fatigue life prediction of a wing-fuselage lug joint attachment bracket on a transport aircraft. Finite element analysis was used to analyze the stresses on the bracket under bending loads from the wing. The maximum stress of 919 MPa was found at the lug hole. Fatigue life calculation was then performed using the local stress history to predict fatigue crack initiation and propagation at high stress locations. The analysis provides important data to ensure the lug joint bracket can withstand the flight loads without failure throughout the intended lifespan of the aircraft.
Modeling and analysis of outer shell of cruise missileeSAT Journals
Abstract The advent of the modern cruise missile, with less radar detection and the ability to fly at low altitudes in sub sonic speeds with
precise navigation, placed an extensive liability on all weapon systems in defence.The purpose of this project is to present a
preliminary analysis and design of a cruise missile which fulfill the mission requirements. This design project comprises the concept
exploration and development stages of the full design process. While designing we should take dimensions as per our requirements and
should have tolerances to design parts. CATIA V5 is used as design tool. The inlet temperature, pressure, density and altitude are the
parameters to analyze the flow properties. The analysis done in the ANSYS WORKBENCH 14.5.This paper discuss the flow of the
designed model. In this paper we are going to discuss key aspects in aerodynamics of wing and fin.
Keywords: Wing, Fin, Pressure, Density, Altitude, Aerodynamics
- The document is a seminar paper on aircraft drag reduction techniques presented by Dhanashree M. Waghmare and guided by Prof. V. A. Yevalikar. It includes sections on literature review, aims and objectives, introduction to basic aerodynamic principles, aircraft wing terminology, forces on aircraft, types of drag, factors affecting drag, and methods to reduce drag. The paper discusses drag reduction techniques like increasing wing aspect ratio, wing tip devices, vortex generators, and laminar flow control. It concludes with future areas of research like friction drag reduction at supersonic speeds and circulation control using auxiliary power.
Numerical analysis on effect of exit blade angle on cavitation in centrifuIAEME Publication
This document presents a numerical analysis of the effect of exit blade angle on cavitation in a centrifugal pump. A centrifugal pump test rig was modeled in Creo Parametric with impellers having different exit blade angles. Computational fluid dynamics simulations were performed in ANSYS CFX to analyze cavitation at various flow rates. The results show that higher exit blade angles experience more cavitation in the form of vapor formation. Pressure contours also indicate lower pressures develop at higher exit blade angles. Therefore, a centrifugal pump impeller with a lower exit blade angle is less susceptible to cavitation issues.
This document is a seminar report submitted by Dhanashree Manohar Waghmare on aircraft drag reduction techniques. The report contains an introduction on the importance of reducing aircraft drag. It then provides a literature review on relevant topics like aerodynamics, fluid mechanics, previous studies on drag reduction. The objectives are to study aerodynamic principles, forces on aircraft, types of drag and reduction methods. The body of the report discusses these topics in detail with diagrams. It covers concepts like aerodynamics, aircraft wings, forces, types of drag and techniques to reduce skin friction, lift-induced and wave drag. The report aims to provide a comprehensive overview of aircraft drag and methods to reduce it.
IRJET- Aerodynamic Performance Analysis on a Wing with “M” Shaped Serrate...IRJET Journal
1. Researchers analyzed the aerodynamic performance of a wing with an "M" shaped serrated trailing edge using wind tunnel testing.
2. Results showed that the serrated trailing edge design produced up to 25% more lift and 61% less drag compared to a normal wing at certain angles of attack.
3. The maximum improvement in lift-to-drag ratio occurred at an angle of attack of 10 degrees. The study demonstrates that the "M" shaped serrated trailing edge can enhance the aerodynamic performance of wings.
Numerical Investigation Of Compression Performance Of Different Blade Configu...IJERA Editor
This project work is to investigate the compression efficiency of different configuration of Turbo-Prop Co-Rotor Blade System of Subsonic Axial Flow Compressor. By this method the highly compressed air can be passed over the intake of the engine to the compressor with high mass flow rate in change of low velocity and high pressure ratio. The length of the small rotor is varied in terms of large rotor length by 25,50 & 75% . Each will have three space configuration in terms of diameter of rotor and in the percentage of 5,10,15%. A total of 12 configurations will be simulated to arrive optimum blade configuration. The blades are made in the shape of an airfoil like wing of an aircraft. The engine rotates the propeller blades, which produce lift. This lift is called thrust and moves the aircraft forward. Blades are usually made of high lift airfoil which allows more rotation to generate high pressure for engine. ANSYS- Fluent is commercial software which is robust for most of the fluid dynamic problems and it is used in this project work to evaluate the different configurations of co-rotor propeller system to arrive the best.
Analysis and Estimation of Stiffness of Outer Race of Aircraft Bearingspaperpublications3
The document analyzes and estimates the stiffness of the outer race of aircraft bearings. It describes how a bearing outer race was modeled and analyzed in CREO and ANSYS software to determine its deflection and stiffness when subjected to radial loads. The results found a stiffness value of 769.23 kN/mm which was verified through theoretical calculations to be within acceptable limits for aircraft bearing materials.
This document summarizes a computational fluid dynamics (CFD) analysis of flow separation control over an airfoil using a co-flow jet technique. The co-flow jet concept injects a high-velocity jet near the leading edge and sucks air near the trailing edge to enhance mixing and allow the flow to remain attached at high angles of attack. CFD simulations found that the co-flow jet airfoil significantly increased maximum lift, increased stall angle by 5 degrees, and expanded the operating range by 38%. While drag was higher for the co-flow jet airfoil, its lift-to-drag ratio was also much larger, indicating improved aerodynamic efficiency overall. The co-flow jet technique was found to effectively delay flow
Stringers are longitudinal stiffening members that support aircraft skin and prevent buckling. They transfer loads between the skin and supporting structures like frames and ribs. Stringers are commonly made of aluminum alloy and come in different cross-sectional shapes. Current research is optimizing stringer design and implementing designs in CAD software to minimize weight while ensuring strength and stability. Future work could extend the design methodology to include multiple cracks, fasteners instead of adhesive, drag forces, and design of the full wing box.
Impact of Ground Effect on Circulation Controlled Cylindrical SurfacesCSCJournals
Circulation control technology and motion in close proximity to the ground have both shown aerodynamic benefits in the generation of lift. Recent research efforts at West Virginia University have explored the potential of merging the two phenomena, in an attempt to enhance both technologies. This paper initiates this combined effort by experimentally investigating the impact ground effect has on the separation location of a jet blown tangentially over circulation controlled cylindrical surfaces. Previous experimental research on circulation controlled cylinders found an optimal radius of curvature and volumetric flow rate; whose model and optimal findings are built upon by this work through the addition of ground effect analysis by varying the ground height. The experiment investigates some of the variables that individually influence circulation control and ground effect; the variables are the radius of curvature, velocity of the jet, and the height from the ground. Data analysis revealed that for a constant volumetric flow rate and varying the height to radius (h/r) value, there is a large amount of variability in the data, indicating that the proximity of the ground has significant impact on the separation location and consequently influence on the potential lift characteristics. Furthermore, when this flow rate was analyzed, it was found that at an h/r of approximately 4.8, it appears that an optimal h/r occurs, based on the surface pressure and flow separation from the cylinders when not influenced by the ground. The data also found that at both radii, 0.520 and 0.659 inches, showed benefit when tested in close proximity to the ground. The findings demonstrate that there is further enhancement potential of the lift generating capability by uniting the lift enhancement of circulation control methodology with the ground effect flight regime. This effort is a preliminary study of a larger effort to determine if merging the two phenomena indicates a lift enhancement. This model does not have a free stream velocity, and subsequently does not measure lift, however, the findings depicted in this effort indicate that there is potential for enhancement, which is currently being researched by the authors.
Light Aircraft Landing Gear Strut Group 6 ReportRobert Tanner
The document analyzes materials for the landing gear strut of a Cessna TTX light aircraft. It translates design requirements into constraints and objectives, screens materials based on compressive strength and corrosion resistance, ranks materials based on indices that minimize weight and maximize buckling resistance and fatigue endurance. Magnesium alloy is selected as it is lightweight, inexpensive, and easier to manufacture than aluminum alloys, though composites are increasingly common in aircraft.
The document discusses force balances used to measure aerodynamic forces on aircraft models in wind tunnels. A one-component balance can measure lift, while a three-component balance can measure lift, drag and pitching moment. The most advanced, a six-component balance, can measure all three forces and three moments to determine an aircraft's motion through air. It then describes a simple mechanical method using weights on a lever arm to measure lift on a wing model, illustrating the basic principles of force balances. More sophisticated electronic instrumentation is needed for accurate measurements in full-scale wind tunnels.
Smoothness running of train on uneven tracks with the help of air springsIAEME Publication
This document summarizes research on using air springs instead of helical springs in train suspension systems. Air springs provide several advantages over helical springs, including maintaining a constant vehicle height under changing loads, improved ride comfort, and increased vehicle speed potential. The document describes the working principle of pneumatic suspension systems using air springs and presents results from experimental testing of air spring characteristics, including vertical and lateral stiffness measurements. It is concluded that air springs have a significantly longer life cycle than helical springs, helping to reduce maintenance costs for transportation systems.
Morphing of Aircraft Wings
This document discusses morphing technology for aircraft wings. Morphing allows wings to change shape to better match flight conditions. It can improve performance, efficiency, and adaptability. Wing morphing technologies include folding, sweeping, extending wings, and changing camber. This allows control of wing area, aspect ratio, and sweep angle. Shape memory alloys are used for actuation components. Advantages of morphing wings include improved performance, control, stealth, reduced drag and weight. Challenges remain in developing morphing wing technologies that can withstand flight conditions.
The document discusses numerical analysis of variable sweep wings for micro air vehicles (MAVs). It presents computational fluid dynamics (CFD) simulations of MAV models with wings swept at 15° and 40° at various angles of attack. The results show that increasing sweep angle decreases parasite drag and improves aerodynamic performance. A sweep angle of 15° provided the best lift-to-drag ratio at low speeds. Swept wings can help MAVs operate efficiently over a range of speeds and angles of attack.
IRJET-Subsonic Flow Study and Analysis on Rotating Cylinder AirfoilIRJET Journal
This document presents a study on modifying the lift characteristics of a conventional symmetrical airfoil (NACA 0012) by adding a rotating cylinder. A numerical analysis and computational fluid dynamics simulation were conducted. Two cases were considered: a cylinder with 13mm diameter located at the 0.125 chord point, and a 15mm cylinder at the 0.25 chord point. The presence of a rotating cylinder was found to significantly increase the airfoil's lift at zero angle of attack through momentum injection, by up to 100%. It also delayed stall characteristics. The document outlines the methodology, including the airfoil geometry, range of air velocities and cylinder rotation speeds studied, and equations used to model static and total pressure.
This document analyzes the aerodynamic performance of blended winglets on aircraft wings through computational fluid dynamics modeling. It finds that winglets can increase the lift to drag ratio of wings by 6-15% compared to wings without winglets. The maximum efficiency occurs at a winglet cant angle of 45 degrees and an angle of attack of 4 degrees. CFD simulations are validated against experimental data and show good agreement on lift coefficient values. Winglets improve efficiency by reducing wingtip vortices and increasing effective aspect ratio without adding structural weight.
Fatigue life estimation of rear fuselage structure of an aircrafteSAT Journals
This document summarizes a study on estimating the fatigue life of the rear fuselage structure of an aircraft. The researchers created a finite element model of the rear fuselage structure in CATIA and analyzed it in MSC.PATRAN and MSC.NASTRAN to identify high stress regions. They found the maximum stress locations were at cut-out corners and rivet holes in the skin. A local model with finer meshing around the cargo door cut-out was also analyzed. Fatigue life was then estimated using Miner's rule and an S-N curve, accounting for factors like surface roughness and reliability. Damage was accumulated over the expected load cycles to predict fatigue life until crack initiation.
Abstract Joined wing layout UAVs feature multiple advantages compared to the rest of UAVs. Their best advantage is the maneuverability. The report contains the analysis of the applicable UAV maneuvers and their application in various flight missions. Keywords: UAV, Joined Wing, Maneuverability
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology
The document discusses design modifications and enhancements to the adaptability of mooring structures for medium-sized aerostats. It proposes three main modifications:
1) Mounting a bearing at the top of the mooring tower to eliminate twisting moments and reduce stresses.
2) Making the air bag frame adjustable to provide constant cushioned support to the balloon and keep it horizontal.
3) Fastening length pieces to allow the same structure to moor balloons of different sizes. Finite element analysis demonstrates that the modifications significantly reduce stresses on the structure.
Stress analysis and fatigue life prediction of wing fuselage lug joint attac...eSAT Publishing House
This document summarizes a study that performed stress analysis and fatigue life prediction of a wing-fuselage lug joint attachment bracket on a transport aircraft. Finite element analysis was used to analyze the stresses on the bracket under bending loads from the wing. The maximum stress of 919 MPa was found at the lug hole. Fatigue life calculation was then performed using the local stress history to predict fatigue crack initiation and propagation at high stress locations. The analysis provides important data to ensure the lug joint bracket can withstand the flight loads without failure throughout the intended lifespan of the aircraft.
Modeling and analysis of outer shell of cruise missileeSAT Journals
Abstract The advent of the modern cruise missile, with less radar detection and the ability to fly at low altitudes in sub sonic speeds with
precise navigation, placed an extensive liability on all weapon systems in defence.The purpose of this project is to present a
preliminary analysis and design of a cruise missile which fulfill the mission requirements. This design project comprises the concept
exploration and development stages of the full design process. While designing we should take dimensions as per our requirements and
should have tolerances to design parts. CATIA V5 is used as design tool. The inlet temperature, pressure, density and altitude are the
parameters to analyze the flow properties. The analysis done in the ANSYS WORKBENCH 14.5.This paper discuss the flow of the
designed model. In this paper we are going to discuss key aspects in aerodynamics of wing and fin.
Keywords: Wing, Fin, Pressure, Density, Altitude, Aerodynamics
- The document is a seminar paper on aircraft drag reduction techniques presented by Dhanashree M. Waghmare and guided by Prof. V. A. Yevalikar. It includes sections on literature review, aims and objectives, introduction to basic aerodynamic principles, aircraft wing terminology, forces on aircraft, types of drag, factors affecting drag, and methods to reduce drag. The paper discusses drag reduction techniques like increasing wing aspect ratio, wing tip devices, vortex generators, and laminar flow control. It concludes with future areas of research like friction drag reduction at supersonic speeds and circulation control using auxiliary power.
Numerical analysis on effect of exit blade angle on cavitation in centrifuIAEME Publication
This document presents a numerical analysis of the effect of exit blade angle on cavitation in a centrifugal pump. A centrifugal pump test rig was modeled in Creo Parametric with impellers having different exit blade angles. Computational fluid dynamics simulations were performed in ANSYS CFX to analyze cavitation at various flow rates. The results show that higher exit blade angles experience more cavitation in the form of vapor formation. Pressure contours also indicate lower pressures develop at higher exit blade angles. Therefore, a centrifugal pump impeller with a lower exit blade angle is less susceptible to cavitation issues.
This document is a seminar report submitted by Dhanashree Manohar Waghmare on aircraft drag reduction techniques. The report contains an introduction on the importance of reducing aircraft drag. It then provides a literature review on relevant topics like aerodynamics, fluid mechanics, previous studies on drag reduction. The objectives are to study aerodynamic principles, forces on aircraft, types of drag and reduction methods. The body of the report discusses these topics in detail with diagrams. It covers concepts like aerodynamics, aircraft wings, forces, types of drag and techniques to reduce skin friction, lift-induced and wave drag. The report aims to provide a comprehensive overview of aircraft drag and methods to reduce it.
IRJET- Aerodynamic Performance Analysis on a Wing with “M” Shaped Serrate...IRJET Journal
1. Researchers analyzed the aerodynamic performance of a wing with an "M" shaped serrated trailing edge using wind tunnel testing.
2. Results showed that the serrated trailing edge design produced up to 25% more lift and 61% less drag compared to a normal wing at certain angles of attack.
3. The maximum improvement in lift-to-drag ratio occurred at an angle of attack of 10 degrees. The study demonstrates that the "M" shaped serrated trailing edge can enhance the aerodynamic performance of wings.
Numerical Investigation Of Compression Performance Of Different Blade Configu...IJERA Editor
This project work is to investigate the compression efficiency of different configuration of Turbo-Prop Co-Rotor Blade System of Subsonic Axial Flow Compressor. By this method the highly compressed air can be passed over the intake of the engine to the compressor with high mass flow rate in change of low velocity and high pressure ratio. The length of the small rotor is varied in terms of large rotor length by 25,50 & 75% . Each will have three space configuration in terms of diameter of rotor and in the percentage of 5,10,15%. A total of 12 configurations will be simulated to arrive optimum blade configuration. The blades are made in the shape of an airfoil like wing of an aircraft. The engine rotates the propeller blades, which produce lift. This lift is called thrust and moves the aircraft forward. Blades are usually made of high lift airfoil which allows more rotation to generate high pressure for engine. ANSYS- Fluent is commercial software which is robust for most of the fluid dynamic problems and it is used in this project work to evaluate the different configurations of co-rotor propeller system to arrive the best.
Analysis and Estimation of Stiffness of Outer Race of Aircraft Bearingspaperpublications3
The document analyzes and estimates the stiffness of the outer race of aircraft bearings. It describes how a bearing outer race was modeled and analyzed in CREO and ANSYS software to determine its deflection and stiffness when subjected to radial loads. The results found a stiffness value of 769.23 kN/mm which was verified through theoretical calculations to be within acceptable limits for aircraft bearing materials.
This document summarizes a computational fluid dynamics (CFD) analysis of flow separation control over an airfoil using a co-flow jet technique. The co-flow jet concept injects a high-velocity jet near the leading edge and sucks air near the trailing edge to enhance mixing and allow the flow to remain attached at high angles of attack. CFD simulations found that the co-flow jet airfoil significantly increased maximum lift, increased stall angle by 5 degrees, and expanded the operating range by 38%. While drag was higher for the co-flow jet airfoil, its lift-to-drag ratio was also much larger, indicating improved aerodynamic efficiency overall. The co-flow jet technique was found to effectively delay flow
Stringers are longitudinal stiffening members that support aircraft skin and prevent buckling. They transfer loads between the skin and supporting structures like frames and ribs. Stringers are commonly made of aluminum alloy and come in different cross-sectional shapes. Current research is optimizing stringer design and implementing designs in CAD software to minimize weight while ensuring strength and stability. Future work could extend the design methodology to include multiple cracks, fasteners instead of adhesive, drag forces, and design of the full wing box.
Impact of Ground Effect on Circulation Controlled Cylindrical SurfacesCSCJournals
Circulation control technology and motion in close proximity to the ground have both shown aerodynamic benefits in the generation of lift. Recent research efforts at West Virginia University have explored the potential of merging the two phenomena, in an attempt to enhance both technologies. This paper initiates this combined effort by experimentally investigating the impact ground effect has on the separation location of a jet blown tangentially over circulation controlled cylindrical surfaces. Previous experimental research on circulation controlled cylinders found an optimal radius of curvature and volumetric flow rate; whose model and optimal findings are built upon by this work through the addition of ground effect analysis by varying the ground height. The experiment investigates some of the variables that individually influence circulation control and ground effect; the variables are the radius of curvature, velocity of the jet, and the height from the ground. Data analysis revealed that for a constant volumetric flow rate and varying the height to radius (h/r) value, there is a large amount of variability in the data, indicating that the proximity of the ground has significant impact on the separation location and consequently influence on the potential lift characteristics. Furthermore, when this flow rate was analyzed, it was found that at an h/r of approximately 4.8, it appears that an optimal h/r occurs, based on the surface pressure and flow separation from the cylinders when not influenced by the ground. The data also found that at both radii, 0.520 and 0.659 inches, showed benefit when tested in close proximity to the ground. The findings demonstrate that there is further enhancement potential of the lift generating capability by uniting the lift enhancement of circulation control methodology with the ground effect flight regime. This effort is a preliminary study of a larger effort to determine if merging the two phenomena indicates a lift enhancement. This model does not have a free stream velocity, and subsequently does not measure lift, however, the findings depicted in this effort indicate that there is potential for enhancement, which is currently being researched by the authors.
Light Aircraft Landing Gear Strut Group 6 ReportRobert Tanner
The document analyzes materials for the landing gear strut of a Cessna TTX light aircraft. It translates design requirements into constraints and objectives, screens materials based on compressive strength and corrosion resistance, ranks materials based on indices that minimize weight and maximize buckling resistance and fatigue endurance. Magnesium alloy is selected as it is lightweight, inexpensive, and easier to manufacture than aluminum alloys, though composites are increasingly common in aircraft.
The document discusses force balances used to measure aerodynamic forces on aircraft models in wind tunnels. A one-component balance can measure lift, while a three-component balance can measure lift, drag and pitching moment. The most advanced, a six-component balance, can measure all three forces and three moments to determine an aircraft's motion through air. It then describes a simple mechanical method using weights on a lever arm to measure lift on a wing model, illustrating the basic principles of force balances. More sophisticated electronic instrumentation is needed for accurate measurements in full-scale wind tunnels.
Smoothness running of train on uneven tracks with the help of air springsIAEME Publication
This document summarizes research on using air springs instead of helical springs in train suspension systems. Air springs provide several advantages over helical springs, including maintaining a constant vehicle height under changing loads, improved ride comfort, and increased vehicle speed potential. The document describes the working principle of pneumatic suspension systems using air springs and presents results from experimental testing of air spring characteristics, including vertical and lateral stiffness measurements. It is concluded that air springs have a significantly longer life cycle than helical springs, helping to reduce maintenance costs for transportation systems.
Morphing of Aircraft Wings
This document discusses morphing technology for aircraft wings. Morphing allows wings to change shape to better match flight conditions. It can improve performance, efficiency, and adaptability. Wing morphing technologies include folding, sweeping, extending wings, and changing camber. This allows control of wing area, aspect ratio, and sweep angle. Shape memory alloys are used for actuation components. Advantages of morphing wings include improved performance, control, stealth, reduced drag and weight. Challenges remain in developing morphing wing technologies that can withstand flight conditions.
The document discusses numerical analysis of variable sweep wings for micro air vehicles (MAVs). It presents computational fluid dynamics (CFD) simulations of MAV models with wings swept at 15° and 40° at various angles of attack. The results show that increasing sweep angle decreases parasite drag and improves aerodynamic performance. A sweep angle of 15° provided the best lift-to-drag ratio at low speeds. Swept wings can help MAVs operate efficiently over a range of speeds and angles of attack.
IRJET-Subsonic Flow Study and Analysis on Rotating Cylinder AirfoilIRJET Journal
This document presents a study on modifying the lift characteristics of a conventional symmetrical airfoil (NACA 0012) by adding a rotating cylinder. A numerical analysis and computational fluid dynamics simulation were conducted. Two cases were considered: a cylinder with 13mm diameter located at the 0.125 chord point, and a 15mm cylinder at the 0.25 chord point. The presence of a rotating cylinder was found to significantly increase the airfoil's lift at zero angle of attack through momentum injection, by up to 100%. It also delayed stall characteristics. The document outlines the methodology, including the airfoil geometry, range of air velocities and cylinder rotation speeds studied, and equations used to model static and total pressure.
Fluid-Structure Interaction Over an Aircraft WingIJERDJOURNAL
ABSTRACT:- Aircraft is a brilliant man-made structure which helps us to fly over the world. At the same time, aircraft is a complex structure to be checked and maintained for the aero elasticity due to aerodynamic properties. In this paper, the fluid-structure interaction problem in super critical NASA SC(2)-0412 airfoil is discussed. The main aim of this project is to find the best performance and deformation limit of the wing on different Mach numbers. This project is completely done by numerical methods of designing the wing using CATIA and flow properties in Computational Fluid Dynamics (CFD) method. Finally, the structural analysis for deformation is analysed in ANSYS. The analytical approach of fluid-structure interaction over an Aircraft wing is complex.
The document summarizes a computational fluid dynamics study of flow over clean and loaded wings using ANSYS Fluent. It describes simulating flow over an airfoil at angles from 0-20 degrees both with and without a missile model attached. The results show that boundary layer separation begins around 15 degrees for the clean wing and occurs at a lower angle for the loaded wing. However, issues with meshing prevented analysis of the loaded wing case. Increasing angle of attack was found to increase lift forces until stall occurred due to vortex shedding beyond 20 degrees.
This paper summarizes a computational fluid dynamics study of the aerodynamic performance of different front wing designs for a Formula SAE race car. The study used RANS simulations to analyze the downforce and drag produced by variations in the angle of attack and spacing of the wing elements. The results showed that a 5 degree angle of attack optimized the downforce to drag ratio. Increasing the spacing between wing elements also increased downforce by allowing momentum from one element to interact with the next element's boundary layer. Future work could involve parameterizing the wing geometry for shape optimization to further improve performance.
THE EFFECT OF VARIATION SKEW ANGLE B-SERIES PROPELLER ON PERFORMANCE AND CAVI...IAEME Publication
Achieving the highest possible efficiency from a propeller is needed to minimize
fuel. However, this is limited by the occurrence of cavitation, vibration, noise and
material strength possessed by propellers. Thus it is necessary to do a new
breakthrough in designing or modifying the shape of the propeller to achieve
maximum performance. One modification that can be done is to change the skew
angle. Propeller B-Series is a propeller that is often used and has a fairly complete
geometry data. Cavitation is something that must be considered because it will
manifest into noise, vibration and erosion in the propeller blade. The modification of
the skew angle will be analyzed using the CFD (Computational Fluid Dynamics)
method of how the relationship between performance and cavitation results from the
various variations that have been made. So that later it can be known that skew angles
produce maximum performance and low cavitation. From the simulation results it can
be concluded that the greater the skew angle, the value of the thrust and torque
Study of Flow Over Supercritical Airfoil and it’s Comparison with NACA AirfoilIRJET Journal
This document discusses and compares supercritical airfoils to conventional NACA airfoils. It was created in the 1960s by Dr. Richard Whitcomb to reduce transonic drag on aircraft cruising near the speed of sound. Supercritical airfoils have an inverted shape with a flat upper surface and curved lower surface, delaying shockwave formation. Computational fluid dynamics analysis shows supercritical airfoils produce weaker shockwaves at higher speeds than NACA airfoils, reducing drag. Today, nearly all transonic aircraft use supercritical airfoils to improve efficiency.
Transient flow analysis for horizontal axial upper-wind turbineinventy
This study is to carry out a transient flow field analysis on the condition that the wind turbine is working to generate turbine, the wind turbine operating conditions change over time, Purpose of this study is try to find out the rule from the wind turbine changing over time . In transient analysis, the wind velocity on inlet boundary and rotation speed in the rotor field will change over time, and an analytical process is provided that can be used for future reference. At present, the wind turbine model is designed on the concept of upwind horizontal axis type. The computer engineering software GH Bladed is used to obtain the relationship between the rotor velocity and the wind turbine. Then the ANSYS engineering software is used to calculate the stress and strain distribution in the blades over time. From the analytical result, the relationship between the stress distribution in the blades and the rotor velocity is got to be used as a reference for future wind turbine structural optimization.
Strategic design of aircraft wings have evolved over time for maximum fuel efficiency. One of such ideas involves winglet which has been known
to reduce turbulence at the tip of the wings. This study intends to investigate the
differences in drag and lift forces generated at aeroplane wings with and without winglet at cruising speed using FEM. Simulations were performed in the
SST turbulence model of CFD and the results are compared to that of the experimental and theoretical models. The simulation showed that the lift increased
by 26.0% and the drag decreased by 74.6% for the winglet at cruising speed.
This study investigates unsteady aerodynamic effects for a vertical axial wind turbine through computational fluid dynamics simulations. A two-dimensional model of the turbine was created using a NACA0015 airfoil for the blades. Simulations were run at different tip speed ratios to analyze blade forces, torque, and dynamic stall. Results showed that maximum average torque occurred at a tip speed ratio of 1.3. Blade forces were highest when the rotor was at 50 degrees. Dynamic stall phenomena, such as vortex shedding and detachment, were observed and affected turbine performance.
IRJET- Development of High-Lift Laminar Wing using Steady Active Flow ControlIRJET Journal
This document summarizes a study that investigated using active flow control (AFC) to develop a high-lift laminar wing. AFC was tested from different slot locations at varying momentum coefficients to determine its effect on lift and drag. The most effective case used unequal blowing from the leading and trailing edge slots, increasing lift by 31-43% compared to the baseline wing without AFC. However, these lift increases were lower than other studies. Pressure distributions showed that AFC helped reenergize the boundary layer and prevent flow separation at higher angles of attack. While encouraging, further investigation is needed to fully realize the potential of AFC for improving the high-lift capability of laminar wings.
CFD Analysis Of Savonius Vertical Axis Wind Turbine: A ReviewIRJET Journal
This document reviews computational fluid dynamics (CFD) analysis of the Savonius vertical axis wind turbine. It discusses how CFD provides a less expensive and time-consuming alternative to experimental testing of wind turbine designs and configurations. The document outlines different CFD methods used like steady-state and transient simulations. It also summarizes key factors that affect Savonius turbine performance according to previous studies, such as aspect ratio, overlap ratio, number of blades, and influence of the stator and Reynolds number.
M.Goman, A.Khramtsovsky, Y.Patel (2003) - Modeling and Analysis of Aircraft S...Project KRIT
М.Г.Гоман, А.В.Храмцовский, Йоуг Патель «Моделирование и анализ режимов штопора самолёта, обусловленных аэродиномической асимметрией», проект доклада на конференции AIAA, 2003 г.
M.Goman, A.Khramtsovsky, Y.Patel "Modeling and Analysis of Aircraft Spin Produced by Aerodynamic Asymmetry", draft AIAA paper, 2003
Modal, Fatigue and Fracture Analysis of Wing Fuselage Lug Joint Bracket for a...IRJET Journal
This document summarizes a study on the modal, fatigue, and fracture analysis of a wing fuselage lug joint bracket for a transport aircraft. Finite element analysis was conducted in ANSYS to determine the modal frequencies and stress distributions. The first six natural frequencies were identified. Fatigue analysis using the Goodman diagram estimated the fatigue life to be 1 million cycles, qualifying it as a high cycle fatigue case. Fracture mechanics analysis identified maximum stresses near rivet holes and predicted crack initiation. The finite element analysis results for stresses, frequencies, and fatigue life were validated using analytical methods. The study aimed to understand the dynamic behavior and improve the structural integrity of the wing attachment point.
CFD Analysis of Delta Winged Aircraft – A ReviewIRJET Journal
This document reviews computational fluid dynamics (CFD) analysis that has been conducted on delta wing aircraft and airfoils with surface modifications like dimples. Several studies are summarized that used CFD to analyze how dimples affect lift and drag on airfoils at various angles of attack. Dimples function similarly to vortex generators by creating vortices that delay flow separation and reduce pressure drag. Researchers have found that dimples can increase an aircraft's aerodynamic performance characteristics and maneuverability by reducing drag and stall. The document reviews multiple studies that analyzed different dimple shapes and configurations on symmetric and asymmetric airfoil profiles.
Numerical Analysis of Lift & Drag Performance of NACA0012 Wind Turbine AerofoilIRJET Journal
This document discusses numerical analysis of lift and drag performance for a NACA0012 wind turbine airfoil. Two airfoil models were analyzed: one with a regular surface and another with circular dimples added to the upper surface. Computational fluid dynamics software was used to calculate the coefficient of lift and drag at various angles of attack. The results showed that adding dimples to the upper surface increased the lift to drag ratio compared to the regular airfoil surface, indicating improved aerodynamic performance from controlling flow separation with the dimples.
This document summarizes the design, construction, and testing of a flexible wind turbine blade. The blade was designed to passively control the rotor and reduce aerodynamic loads through deformation in response to changing wind speeds. A curved blade geometry was modeled and tested on a small scale wind turbine rotor. Both static and dynamic tests were performed and results compared to a rigid blade rotor. The flexible blade achieved the intended deformation and changes in pitch angle to better control the rotor across a range of wind speeds.
The document proposes designing and building a car-mounted thrust stand for dynamic testing of propellers as an alternative to traditional wind tunnel testing. Key details include:
- The setup would allow testing of propellers over 10 inches in diameter, which most universities cannot test in wind tunnels.
- Aerodynamic considerations require the propeller to be at least 5 times its diameter from the car roof to avoid blockage, and the largest propeller to be tested is 10 inches so the minimum height is set at 27 inches.
- Structural analysis shows the design has a safety factor of at least 1.6 under worst-case loads to remain safely attached to the car at high speeds.
Estimation of water momentum and propeller velocity in bow thruster model of...IJECEIAES
Autonomous surface vehicle (ASV) is a vehicle in the form of an unmanned on-water surface vessel that can move automatically. As such, an automatic control system is essentially required. The bow thruster system functions as a propulsion control device in its operations. In this research, the water momentum and propeller velocity were estimated based on the dynamic bow thruster model. The estimation methods used is the Kalman filter (KF) and ensemble Kalman filter (EnKF). There are two scenarios: tunnel thruster condition and open-bladed thruster condition. The estimation results in the tunnel thruster condition showed that the root mean square error (RMSE) by the EnKF method was relatively smaller, that is, 0.7920 and 0.1352, while the estimation results in the open-bladed thruster condition showed that the RMSE by the KF method was relatively smaller, that is, 1.9957 and 2.0609.
Determination of Flutter Angle by Resolving Effective Gyroscope Couple to Ret...IRJET Journal
The document discusses determining flutter angles for an airplane by resolving effective gyroscope couples. It presents a control algorithm that uses gyroscope measurements as inputs to predict flutter angles based on conditional statements. A Rayleigh-Ritz beam model and finite element model are developed to model the wing and wingtip fin. Flight tests show the robot can hover using feedback from either motion capture or gyroscope measurements of angular velocity, though position errors are larger when using full attitude estimates from the gyroscope due to drift in the pitch axis estimate.
Similar to VORTEX DYNAMIC INVESTIGATION OF WING SLOTTED GAP OF SAAB JAS GRIPEN C-LIKE FIGHTER (20)
Submission Deadline: 30th September 2022
Acceptance Notification: Within Three Days’ time period
Online Publication: Within 24 Hrs. time Period
Expected Date of Dispatch of Printed Journal: 5th October 2022
MODELING AND ANALYSIS OF SURFACE ROUGHNESS AND WHITE LATER THICKNESS IN WIRE-...IAEME Publication
White layer thickness (WLT) formed and surface roughness in wire electric discharge turning (WEDT) of tungsten carbide composite has been made to model through response surface methodology (RSM). A Taguchi’s standard Design of experiments involving five input variables with three levels has been employed to establish a mathematical model between input parameters and responses. Percentage of cobalt content, spindle speed, Pulse on-time, wire feed and pulse off-time were changed during the experimental tests based on the Taguchi’s orthogonal array L27 (3^13). Analysis of variance (ANOVA) revealed that the mathematical models obtained can adequately describe performance within the parameters of the factors considered. There was a good agreement between the experimental and predicted values in this study.
A STUDY ON THE REASONS FOR TRANSGENDER TO BECOME ENTREPRENEURSIAEME Publication
The study explores the reasons for a transgender to become entrepreneurs. In this study transgender entrepreneur was taken as independent variable and reasons to become as dependent variable. Data were collected through a structured questionnaire containing a five point Likert Scale. The study examined the data of 30 transgender entrepreneurs in Salem Municipal Corporation of Tamil Nadu State, India. Simple Random sampling technique was used. Garrett Ranking Technique (Percentile Position, Mean Scores) was used as the analysis for the present study to identify the top 13 stimulus factors for establishment of trans entrepreneurial venture. Economic advancement of a nation is governed upon the upshot of a resolute entrepreneurial doings. The conception of entrepreneurship has stretched and materialized to the socially deflated uncharted sections of transgender community. Presently transgenders have smashed their stereotypes and are making recent headlines of achievements in various fields of our Indian society. The trans-community is gradually being observed in a new light and has been trying to achieve prospective growth in entrepreneurship. The findings of the research revealed that the optimistic changes are taking place to change affirmative societal outlook of the transgender for entrepreneurial ventureship. It also laid emphasis on other transgenders to renovate their traditional living. The paper also highlights that legislators, supervisory body should endorse an impartial canons and reforms in Tamil Nadu Transgender Welfare Board Association.
BROAD UNEXPOSED SKILLS OF TRANSGENDER ENTREPRENEURSIAEME Publication
Since ages gender difference is always a debatable theme whether caused by nature, evolution or environment. The birth of a transgender is dreadful not only for the child but also for their parents. The pain of living in the wrong physique and treated as second class victimized citizen is outrageous and fully harboured with vicious baseless negative scruples. For so long, social exclusion had perpetuated inequality and deprivation experiencing ingrained malign stigma and besieged victims of crime or violence across their life spans. They are pushed into the murky way of life with a source of eternal disgust, bereft sexual potency and perennial fear. Although they are highly visible but very little is known about them. The common public needs to comprehend the ravaged arrogance on these insensitive souls and assist in integrating them into the mainstream by offering equal opportunity, treat with humanity and respect their dignity. Entrepreneurship in the current age is endorsing the gender fairness movement. Unstable careers and economic inadequacy had inclined one of the gender variant people called Transgender to become entrepreneurs. These tiny budding entrepreneurs resulted in economic transition by means of employment, free from the clutches of stereotype jobs, raised standard of living and handful of financial empowerment. Besides all these inhibitions, they were able to witness a platform for skill set development that ignited them to enter into entrepreneurial domain. This paper epitomizes skill sets involved in trans-entrepreneurs of Thoothukudi Municipal Corporation of Tamil Nadu State and is a groundbreaking determination to sightsee various skills incorporated and the impact on entrepreneurship.
DETERMINANTS AFFECTING THE USER'S INTENTION TO USE MOBILE BANKING APPLICATIONSIAEME Publication
The banking and financial services industries are experiencing increased technology penetration. Among them, the banking industry has made technological advancements to better serve the general populace. The economy focused on transforming the banking sector's system into a cashless, paperless, and faceless one. The researcher wants to evaluate the user's intention for utilising a mobile banking application. The study also examines the variables affecting the user's behaviour intention when selecting specific applications for financial transactions. The researcher employed a well-structured questionnaire and a descriptive study methodology to gather the respondents' primary data utilising the snowball sampling technique. The study includes variables like performance expectations, effort expectations, social impact, enabling circumstances, and perceived risk. Each of the aforementioned variables has a major impact on how users utilise mobile banking applications. The outcome will assist the service provider in comprehending the user's history with mobile banking applications.
ANALYSE THE USER PREDILECTION ON GPAY AND PHONEPE FOR DIGITAL TRANSACTIONSIAEME Publication
Technology upgradation in banking sector took the economy to view that payment mode towards online transactions using mobile applications. This system enabled connectivity between banks, Merchant and user in a convenient mode. there are various applications used for online transactions such as Google pay, Paytm, freecharge, mobikiwi, oxygen, phonepe and so on and it also includes mobile banking applications. The study aimed at evaluating the predilection of the user in adopting digital transaction. The study is descriptive in nature. The researcher used random sample techniques to collect the data. The findings reveal that mobile applications differ with the quality of service rendered by Gpay and Phonepe. The researcher suggest the Phonepe application should focus on implementing the application should be user friendly interface and Gpay on motivating the users to feel the importance of request for money and modes of payments in the application.
VOICE BASED ATM FOR VISUALLY IMPAIRED USING ARDUINOIAEME Publication
The prototype of a voice-based ATM for visually impaired using Arduino is to help people who are blind. This uses RFID cards which contain users fingerprint encrypted on it and interacts with the users through voice commands. ATM operates when sensor detects the presence of one person in the cabin. After scanning the RFID card, it will ask to select the mode like –normal or blind. User can select the respective mode through voice input, if blind mode is selected the balance check or cash withdraw can be done through voice input. Normal mode procedure is same as the existing ATM.
IMPACT OF EMOTIONAL INTELLIGENCE ON HUMAN RESOURCE MANAGEMENT PRACTICES AMONG...IAEME Publication
There is increasing acceptability of emotional intelligence as a major factor in personality assessment and effective human resource management. Emotional intelligence as the ability to build capacity, empathize, co-operate, motivate and develop others cannot be divorced from both effective performance and human resource management systems. The human person is crucial in defining organizational leadership and fortunes in terms of challenges and opportunities and walking across both multinational and bilateral relationships. The growing complexity of the business world requires a great deal of self-confidence, integrity, communication, conflict and diversity management to keep the global enterprise within the paths of productivity and sustainability. Using the exploratory research design and 255 participants the result of this original study indicates strong positive correlation between emotional intelligence and effective human resource management. The paper offers suggestions on further studies between emotional intelligence and human capital development and recommends for conflict management as an integral part of effective human resource management.
VISUALISING AGING PARENTS & THEIR CLOSE CARERS LIFE JOURNEY IN AGING ECONOMYIAEME Publication
Our life journey, in general, is closely defined by the way we understand the meaning of why we coexist and deal with its challenges. As we develop the "inspiration economy", we could say that nearly all of the challenges we have faced are opportunities that help us to discover the rest of our journey. In this note paper, we explore how being faced with the opportunity of being a close carer for an aging parent with dementia brought intangible discoveries that changed our insight of the meaning of the rest of our life journey.
A STUDY ON THE IMPACT OF ORGANIZATIONAL CULTURE ON THE EFFECTIVENESS OF PERFO...IAEME Publication
The main objective of this study is to analyze the impact of aspects of Organizational Culture on the Effectiveness of the Performance Management System (PMS) in the Health Care Organization at Thanjavur. Organizational Culture and PMS play a crucial role in present-day organizations in achieving their objectives. PMS needs employees’ cooperation to achieve its intended objectives. Employees' cooperation depends upon the organization’s culture. The present study uses exploratory research to examine the relationship between the Organization's culture and the Effectiveness of the Performance Management System. The study uses a Structured Questionnaire to collect the primary data. For this study, Thirty-six non-clinical employees were selected from twelve randomly selected Health Care organizations at Thanjavur. Thirty-two fully completed questionnaires were received.
Living in 21st century in itself reminds all of us the necessity of police and its administration. As more and more we are entering into the modern society and culture, the more we require the services of the so called ‘Khaki Worthy’ men i.e., the police personnel. Whether we talk of Indian police or the other nation’s police, they all have the same recognition as they have in India. But as already mentioned, their services and requirements are different after the like 26th November, 2008 incidents, where they without saving their own lives has sacrificed themselves without any hitch and without caring about their respective family members and wards. In other words, they are like our heroes and mentors who can guide us from the darkness of fear, militancy, corruption and other dark sides of life and so on. Now the question arises, if Gandhi would have been alive today, what would have been his reaction/opinion to the police and its functioning? Would he have some thing different in his mind now what he had been in his mind before the partition or would he be going to start some Satyagraha in the form of some improvement in the functioning of the police administration? Really these questions or rather night mares can come to any one’s mind, when there is too much confusion is prevailing in our minds, when there is too much corruption in the society and when the polices working is also in the questioning because of one or the other case throughout the India. It is matter of great concern that we have to thing over our administration and our practical approach because the police personals are also like us, they are part and parcel of our society and among one of us, so why we all are pin pointing towards them.
A STUDY ON TALENT MANAGEMENT AND ITS IMPACT ON EMPLOYEE RETENTION IN SELECTED...IAEME Publication
The goal of this study was to see how talent management affected employee retention in the selected IT organizations in Chennai. The fundamental issue was the difficulty to attract, hire, and retain talented personnel who perform well and the gap between supply and demand of talent acquisition and retaining them within the firms. The study's main goals were to determine the impact of talent management on employee retention in IT companies in Chennai, investigate talent management strategies that IT companies could use to improve talent acquisition, performance management, career planning and formulate retention strategies that the IT firms could use. The respondents were given a structured close-ended questionnaire with the 5 Point Likert Scale as part of the study's quantitative research design. The target population consisted of 289 IT professionals. The questionnaires were distributed and collected by the researcher directly. The Statistical Package for Social Sciences (SPSS) was used to collect and analyse the questionnaire responses. Hypotheses that were formulated for the various areas of the study were tested using a variety of statistical tests. The key findings of the study suggested that talent management had an impact on employee retention. The studies also found that there is a clear link between the implementation of talent management and retention measures. Management should provide enough training and development for employees, clarify job responsibilities, provide adequate remuneration packages, and recognise employees for exceptional performance.
ATTRITION IN THE IT INDUSTRY DURING COVID-19 PANDEMIC: LINKING EMOTIONAL INTE...IAEME Publication
Globally, Millions of dollars were spent by the organizations for employing skilled Information Technology (IT) professionals. It is costly to replace unskilled employees with IT professionals possessing technical skills and competencies that aid in interconnecting the business processes. The organization’s employment tactics were forced to alter by globalization along with technological innovations as they consistently diminish to remain lean, outsource to concentrate on core competencies along with restructuring/reallocate personnel to gather efficiency. As other jobs, organizations or professions have become reasonably more appropriate in a shifting employment landscape, the above alterations trigger both involuntary as well as voluntary turnover. The employee view on jobs is also afflicted by the COVID-19 pandemic along with the employee-driven labour market. So, having effective strategies is necessary to tackle the withdrawal rate of employees. By associating Emotional Intelligence (EI) along with Talent Management (TM) in the IT industry, the rise in attrition rate was analyzed in this study. Only 303 respondents were collected out of 350 participants to whom questionnaires were distributed. From the employees of IT organizations located in Bangalore (India), the data were congregated. A simple random sampling methodology was employed to congregate data as of the respondents. Generating the hypothesis along with testing is eventuated. The effect of EI and TM along with regression analysis between TM and EI was analyzed. The outcomes indicated that employee and Organizational Performance (OP) were elevated by effective EI along with TM.
INFLUENCE OF TALENT MANAGEMENT PRACTICES ON ORGANIZATIONAL PERFORMANCE A STUD...IAEME Publication
By implementing talent management strategy, organizations would have the option to retain their skilled professionals while additionally working on their overall performance. It is the course of appropriately utilizing the ideal individuals, setting them up for future top positions, exploring and dealing with their performance, and holding them back from leaving the organization. It is employee performance that determines the success of every organization. The firm quickly obtains an upper hand over its rivals in the event that its employees having particular skills that cannot be duplicated by the competitors. Thus, firms are centred on creating successful talent management practices and processes to deal with the unique human resources. Firms are additionally endeavouring to keep their top/key staff since on the off chance that they leave; the whole store of information leaves the firm's hands. The study's objective was to determine the impact of talent management on organizational performance among the selected IT organizations in Chennai. The study recommends that talent management limitedly affects performance. On the off chance that this talent is appropriately management and implemented properly, organizations might benefit as much as possible from their maintained assets to support development and productivity, both monetarily and non-monetarily.
A STUDY OF VARIOUS TYPES OF LOANS OF SELECTED PUBLIC AND PRIVATE SECTOR BANKS...IAEME Publication
Banking regulations act of India, 1949 defines banking as “acceptance of deposits for the purpose of lending or investment from the public, repayment on demand or otherwise and withdrawable through cheques, drafts order or otherwise”, the major participants of the Indian financial system are commercial banks, the financial institution encompassing term lending institutions. Investments institutions, specialized financial institution and the state level development banks, non banking financial companies (NBFC) and other market intermediaries such has the stock brokers and money lenders are among the oldest of the certain variants of NBFC and the oldest market participants. The asset quality of banks is one of the most important indicators of their financial health. The Indian banking sector has been facing severe problems of increasing Non- Performing Assets (NPAs). The NPAs growth directly and indirectly affects the quality of assets and profitability of banks. It also shows the efficiency of banks credit risk management and the recovery effectiveness. NPA do not generate any income, whereas, the bank is required to make provisions for such as assets that why is a double edge weapon. This paper outlines the concept of quality of bank loans of different types like Housing, Agriculture and MSME loans in state Haryana of selected public and private sector banks. This study is highlighting problems associated with the role of commercial bank in financing Small and Medium Scale Enterprises (SME). The overall objective of the research was to assess the effect of the financing provisions existing for the setting up and operations of MSMEs in the country and to generate recommendations for more robust financing mechanisms for successful operation of the MSMEs, in turn understanding the impact of MSME loans on financial institutions due to NPA. There are many research conducted on the topic of Non- Performing Assets (NPA) Management, concerning particular bank, comparative study of public and private banks etc. In this paper the researcher is considering the aggregate data of selected public sector and private sector banks and attempts to compare the NPA of Housing, Agriculture and MSME loans in state Haryana of public and private sector banks. The tools used in the study are average and Anova test and variance. The findings reveal that NPA is common problem for both public and private sector banks and is associated with all types of loans either that is housing loans, agriculture loans and loans to SMES. NPAs of both public and private sector banks show the increasing trend. In 2010-11 GNPA of public and private sector were at same level it was 2% but after 2010-11 it increased in many fold and at present there is GNPA in some more than 15%. It shows the dark area of Indian banking sector.
EXPERIMENTAL STUDY OF MECHANICAL AND TRIBOLOGICAL RELATION OF NYLON/BaSO4 POL...IAEME Publication
An experiment conducted in this study found that BaSO4 changed Nylon 6's mechanical properties. By changing the weight ratios, BaSO4 was used to make Nylon 6. This Researcher looked into how hard Nylon-6/BaSO4 composites are and how well they wear. Experiments were done based on Taguchi design L9. Nylon-6/BaSO4 composites can be tested for their hardness number using a Rockwell hardness testing apparatus. On Nylon/BaSO4, the wear behavior was measured by a wear monitor, pinon-disc friction by varying reinforcement, sliding speed, and sliding distance, and the microstructure of the crack surfaces was observed by SEM. This study provides significant contributions to ultimate strength by increasing BaSO4 content up to 16% in the composites, and sliding speed contributes 72.45% to the wear rate
ROLE OF SOCIAL ENTREPRENEURSHIP IN RURAL DEVELOPMENT OF INDIA - PROBLEMS AND ...IAEME Publication
The majority of the population in India lives in villages. The village is the back bone of the country. Village or rural industries play an important role in the national economy, particularly in the rural development. Developing the rural economy is one of the key indicators towards a country’s success. Whether it be the need to look after the welfare of the farmers or invest in rural infrastructure, Governments have to ensure that rural development isn’t compromised. The economic development of our country largely depends on the progress of rural areas and the standard of living of rural masses. Village or rural industries play an important role in the national economy, particularly in the rural development. Rural entrepreneurship is based on stimulating local entrepreneurial talent and the subsequent growth of indigenous enterprises. It recognizes opportunity in the rural areas and accelerates a unique blend of resources either inside or outside of agriculture. Rural entrepreneurship brings an economic value to the rural sector by creating new methods of production, new markets, new products and generate employment opportunities thereby ensuring continuous rural development. Social Entrepreneurship has the direct and primary objective of serving the society along with the earning profits. So, social entrepreneurship is different from the economic entrepreneurship as its basic objective is not to earn profits but for providing innovative solutions to meet the society needs which are not taken care by majority of the entrepreneurs as they are in the business for profit making as a sole objective. So, the Social Entrepreneurs have the huge growth potential particularly in the developing countries like India where we have huge societal disparities in terms of the financial positions of the population. Still 22 percent of the Indian population is below the poverty line and also there is disparity among the rural & urban population in terms of families living under BPL. 25.7 percent of the rural population & 13.7 percent of the urban population is under BPL which clearly shows the disparity of the poor people in the rural and urban areas. The need to develop social entrepreneurship in agriculture is dictated by a large number of social problems. Such problems include low living standards, unemployment, and social tension. The reasons that led to the emergence of the practice of social entrepreneurship are the above factors. The research problem lays upon disclosing the importance of role of social entrepreneurship in rural development of India. The paper the tendencies of social entrepreneurship in India, to present successful examples of such business for providing recommendations how to improve situation in rural areas in terms of social entrepreneurship development. Indian government has made some steps towards development of social enterprises, social entrepreneurship, and social in- novation, but a lot remains to be improved.
OPTIMAL RECONFIGURATION OF POWER DISTRIBUTION RADIAL NETWORK USING HYBRID MET...IAEME Publication
Distribution system is a critical link between the electric power distributor and the consumers. Most of the distribution networks commonly used by the electric utility is the radial distribution network. However in this type of network, it has technical issues such as enormous power losses which affect the quality of the supply. Nowadays, the introduction of Distributed Generation (DG) units in the system help improve and support the voltage profile of the network as well as the performance of the system components through power loss mitigation. In this study network reconfiguration was done using two meta-heuristic algorithms Particle Swarm Optimization and Gravitational Search Algorithm (PSO-GSA) to enhance power quality and voltage profile in the system when simultaneously applied with the DG units. Backward/Forward Sweep Method was used in the load flow analysis and simulated using the MATLAB program. Five cases were considered in the Reconfiguration based on the contribution of DG units. The proposed method was tested using IEEE 33 bus system. Based on the results, there was a voltage profile improvement in the system from 0.9038 p.u. to 0.9594 p.u.. The integration of DG in the network also reduced power losses from 210.98 kW to 69.3963 kW. Simulated results are drawn to show the performance of each case.
APPLICATION OF FRUGAL APPROACH FOR PRODUCTIVITY IMPROVEMENT - A CASE STUDY OF...IAEME Publication
Manufacturing industries have witnessed an outburst in productivity. For productivity improvement manufacturing industries are taking various initiatives by using lean tools and techniques. However, in different manufacturing industries, frugal approach is applied in product design and services as a tool for improvement. Frugal approach contributed to prove less is more and seems indirectly contributing to improve productivity. Hence, there is need to understand status of frugal approach application in manufacturing industries. All manufacturing industries are trying hard and putting continuous efforts for competitive existence. For productivity improvements, manufacturing industries are coming up with different effective and efficient solutions in manufacturing processes and operations. To overcome current challenges, manufacturing industries have started using frugal approach in product design and services. For this study, methodology adopted with both primary and secondary sources of data. For primary source interview and observation technique is used and for secondary source review has done based on available literatures in website, printed magazines, manual etc. An attempt has made for understanding application of frugal approach with the study of manufacturing industry project. Manufacturing industry selected for this project study is Mahindra and Mahindra Ltd. This paper will help researcher to find the connections between the two concepts productivity improvement and frugal approach. This paper will help to understand significance of frugal approach for productivity improvement in manufacturing industry. This will also help to understand current scenario of frugal approach in manufacturing industry. In manufacturing industries various process are involved to deliver the final product. In the process of converting input in to output through manufacturing process productivity plays very critical role. Hence this study will help to evolve status of frugal approach in productivity improvement programme. The notion of frugal can be viewed as an approach towards productivity improvement in manufacturing industries.
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Rainfall intensity duration frequency curve statistical analysis and modeling...bijceesjournal
Using data from 41 years in Patna’ India’ the study’s goal is to analyze the trends of how often it rains on a weekly, seasonal, and annual basis (1981−2020). First, utilizing the intensity-duration-frequency (IDF) curve and the relationship by statistically analyzing rainfall’ the historical rainfall data set for Patna’ India’ during a 41 year period (1981−2020), was evaluated for its quality. Changes in the hydrologic cycle as a result of increased greenhouse gas emissions are expected to induce variations in the intensity, length, and frequency of precipitation events. One strategy to lessen vulnerability is to quantify probable changes and adapt to them. Techniques such as log-normal, normal, and Gumbel are used (EV-I). Distributions were created with durations of 1, 2, 3, 6, and 24 h and return times of 2, 5, 10, 25, and 100 years. There were also mathematical correlations discovered between rainfall and recurrence interval.
Findings: Based on findings, the Gumbel approach produced the highest intensity values, whereas the other approaches produced values that were close to each other. The data indicates that 461.9 mm of rain fell during the monsoon season’s 301st week. However, it was found that the 29th week had the greatest average rainfall, 92.6 mm. With 952.6 mm on average, the monsoon season saw the highest rainfall. Calculations revealed that the yearly rainfall averaged 1171.1 mm. Using Weibull’s method, the study was subsequently expanded to examine rainfall distribution at different recurrence intervals of 2, 5, 10, and 25 years. Rainfall and recurrence interval mathematical correlations were also developed. Further regression analysis revealed that short wave irrigation, wind direction, wind speed, pressure, relative humidity, and temperature all had a substantial influence on rainfall.
Originality and value: The results of the rainfall IDF curves can provide useful information to policymakers in making appropriate decisions in managing and minimizing floods in the study area.
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Climate change's impact on the planet forced the United Nations and governments to promote green energies and electric transportation. The deployments of photovoltaic (PV) and electric vehicle (EV) systems gained stronger momentum due to their numerous advantages over fossil fuel types. The advantages go beyond sustainability to reach financial support and stability. The work in this paper introduces the hybrid system between PV and EV to support industrial and commercial plants. This paper covers the theoretical framework of the proposed hybrid system including the required equation to complete the cost analysis when PV and EV are present. In addition, the proposed design diagram which sets the priorities and requirements of the system is presented. The proposed approach allows setup to advance their power stability, especially during power outages. The presented information supports researchers and plant owners to complete the necessary analysis while promoting the deployment of clean energy. The result of a case study that represents a dairy milk farmer supports the theoretical works and highlights its advanced benefits to existing plants. The short return on investment of the proposed approach supports the paper's novelty approach for the sustainable electrical system. In addition, the proposed system allows for an isolated power setup without the need for a transmission line which enhances the safety of the electrical network
Comparative analysis between traditional aquaponics and reconstructed aquapon...bijceesjournal
The aquaponic system of planting is a method that does not require soil usage. It is a method that only needs water, fish, lava rocks (a substitute for soil), and plants. Aquaponic systems are sustainable and environmentally friendly. Its use not only helps to plant in small spaces but also helps reduce artificial chemical use and minimizes excess water use, as aquaponics consumes 90% less water than soil-based gardening. The study applied a descriptive and experimental design to assess and compare conventional and reconstructed aquaponic methods for reproducing tomatoes. The researchers created an observation checklist to determine the significant factors of the study. The study aims to determine the significant difference between traditional aquaponics and reconstructed aquaponics systems propagating tomatoes in terms of height, weight, girth, and number of fruits. The reconstructed aquaponics system’s higher growth yield results in a much more nourished crop than the traditional aquaponics system. It is superior in its number of fruits, height, weight, and girth measurement. Moreover, the reconstructed aquaponics system is proven to eliminate all the hindrances present in the traditional aquaponics system, which are overcrowding of fish, algae growth, pest problems, contaminated water, and dead fish.
Batteries -Introduction – Types of Batteries – discharging and charging of battery - characteristics of battery –battery rating- various tests on battery- – Primary battery: silver button cell- Secondary battery :Ni-Cd battery-modern battery: lithium ion battery-maintenance of batteries-choices of batteries for electric vehicle applications.
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This paper describes a speed control device for generating electrical energy on an electricity network based on the doubly fed induction generator (DFIG) used for wind power conversion systems. At first, a double-fed induction generator model was constructed. A control law is formulated to govern the flow of energy between the stator of a DFIG and the energy network using three types of controllers: proportional integral (PI), sliding mode controller (SMC) and second order sliding mode controller (SOSMC). Their different results in terms of power reference tracking, reaction to unexpected speed fluctuations, sensitivity to perturbations, and resilience against machine parameter alterations are compared. MATLAB/Simulink was used to conduct the simulations for the preceding study. Multiple simulations have shown very satisfying results, and the investigations demonstrate the efficacy and power-enhancing capabilities of the suggested control system.
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Car accident rates have increased in recent years, resulting in losses in human lives, properties, and other financial costs. An embedded machine learning-based system is developed to address this critical issue. The system can monitor road conditions, detect driving patterns, and identify aggressive driving behaviors. The system is based on neural networks trained on a comprehensive dataset of driving events, driving styles, and road conditions. The system effectively detects potential risks and helps mitigate the frequency and impact of accidents. The primary goal is to ensure the safety of drivers and vehicles. Collecting data involved gathering information on three key road events: normal street and normal drive, speed bumps, circular yellow speed bumps, and three aggressive driving actions: sudden start, sudden stop, and sudden entry. The gathered data is processed and analyzed using a machine learning system designed for limited power and memory devices. The developed system resulted in 91.9% accuracy, 93.6% precision, and 92% recall. The achieved inference time on an Arduino Nano 33 BLE Sense with a 32-bit CPU running at 64 MHz is 34 ms and requires 2.6 kB peak RAM and 139.9 kB program flash memory, making it suitable for resource-constrained embedded systems.
Applications of artificial Intelligence in Mechanical Engineering.pdfAtif Razi
Historically, mechanical engineering has relied heavily on human expertise and empirical methods to solve complex problems. With the introduction of computer-aided design (CAD) and finite element analysis (FEA), the field took its first steps towards digitization. These tools allowed engineers to simulate and analyze mechanical systems with greater accuracy and efficiency. However, the sheer volume of data generated by modern engineering systems and the increasing complexity of these systems have necessitated more advanced analytical tools, paving the way for AI.
AI offers the capability to process vast amounts of data, identify patterns, and make predictions with a level of speed and accuracy unattainable by traditional methods. This has profound implications for mechanical engineering, enabling more efficient design processes, predictive maintenance strategies, and optimized manufacturing operations. AI-driven tools can learn from historical data, adapt to new information, and continuously improve their performance, making them invaluable in tackling the multifaceted challenges of modern mechanical engineering.
2. Vortex Dynamic Investigation of Wing Slotted Gap of Saab Jas Gripen C-Like Fighter
http://www.iaeme.com/IJMET/index.asp 568 editor@iaeme.com
free velocity (U/U∞) at a value of 0.1. As the AoA increased, the vortex breakdown
location moved forwards, upwards, and moved away from the fuselage.
Keywords : slotted leading edge, outer vortex core, high AoA, laminarize backward.
Cite this Article Sutrisno, Setyawan Bekti Wibowo, Sigit Iswahyudi and Tri Agung
Rohmat, Vortex Dynamic Investigation of Wing Slotted Gap of Saab Jas Gripen C-
Like Fighter, International Journal of Mechanical Engineering and Technology, 10(3),
2019, pp. 567-575.
http://www.iaeme.com/IJMET/issues.asp?JType=IJMET&VType=10&IType=3
1. INTRODUCTION
The delta wing study with computational processes generally uses the κ-ω turbulent model.
The reason is that using a turbulent Shear Stress Transport (SST) κ-ω model will predict high
accuracy flow separation, as the most appropriate choice for delta wing flow [1]–[3]. This
CFD simulation was strengthened by mesh independence test [4].
Zhang et al. have numerically investigated the canard-forward swept aircraft focusing on
interference between canard and wings [5]. Simulation of numerical fighter F-16XL models
for geometry and computational grids with structured and unstructured grids have also been
carried out using delayed detached-eddy simulations, as well as on flight conditions using
fluid dynamics computational near-body CFD / off body hybrid [6]–[8].
Several prominent scientists have investigated several fighters. Boelens has modeled CFD
flow around the X-31 fighter at high AoA [9]. Chen et al. have explored the sideslip effect of
high AoA vortex flow in close pair canard configuration [10]. Ghoreyshi et al. have validated
the simulation of Canard TransCruiser's static and forced flow of motion [11]. Ghoreyshi et
al. have modeled the transonic aerodynamic load of pitching X-31 aircraft [12]. Schütte and
Rein have examined numerically and experimentally unstable simulations around X-31 [13].
The purpose of this paper is to analyze the vortex dynamics of the SAAB JAS Gripen C-
like aircraft model in terms of performance, visualization of flowline above the canard and
wing, streamlined visualization above the canard and wing, streamline above the limiting wall
shear streamline on aircraft surface, wall-pressure distribution as well as pressure and surface
breakdown location. By knowing the characteristics of the dynamic vortex of the SAAB JAS
Gripen C-like aircraft model one can identify its excellence and find suggestions for
improvements that might be sought and improved further towards improving performance and
achievement.
2. RESEARCH METHODS
The model observed in this research was the SAAB JAS Gripen C-Like fighter model, as
shown in Figure 1, with several simplifications in symmetrical models, and several detailed
images, such as antennas. In this research, nets on fighter planes were made by identifying
parts of the plane and then dividing them into several blocks based on changes in the plane's
surface. Hexahedral nets were arranged by changing the size of the net, starting from the part
of the wall as the smallest size and enlarging logarithmic to the outside [8].
The optimal number of cells was obtained by conducting a mesh independence test, as
shown in Table 1. The previous test with 5 million cells, had reached a convergence of lift
strength coefficient values. In the case of this model, the number of cells made was 6,012,908
(~ 6 million). To determine the smallest mesh size on the wall, the y+
value was 4, with the
lowest cell value 0.017 mm.
Dogfighting of the fighter was conducted at slow speeds, i.e. at 0.3 M. When a Mach
number was at a higher value, it caused drag divergence. This was caused by the shock waves
3. Sutrisno, Setyawan Bekti Wibowo, Sigit Iswahyudi and Tri Agung Rohmat
http://www.iaeme.com/IJMET/index.asp 569 editor@iaeme.com
formation at the upper surface of the airfoil, causing flow separation and an adverse pressure
gradient on the back of the wing. Thus the vortex dynamics pattern around the fighter would
be symmetrical, and the calculation was done by a half model to save time. Figure 2 displays
the net and the grid shape above the canard. The computational domain was square with half a
symmetrical model. The boundary conditions in the computational domain were determined,
including the inlet or speed inlet, outlet or pressure outlet, and the symmetrical plane.
Table 1 Mesh independent test for different cell number [14]
Criteria AoA Cl Error
Boelens, 2012 300
1.02157
1.3 million grids 300
1.074078 5.14%
3.1 million grids 300
1.042085 2.01%
5.2 million grids 300
1.026022 0.44%
This study involved several variations of the AoA ranging from 200
to 700
. The flow rate
was set at an inlet velocity of 0.3 M (114. m/s) flowing on the surface of the plane with a
0.08% turbulence intensity. The flow analysis employed the finite volume method based on
the Navier-Stokes equation.
(a) (b)
Figure 1 Geometrical model (a) SAAB JAS Gripen C-like (b) computational domain structure
(modified [14]).
4. Vortex Dynamic Investigation of Wing Slotted Gap of Saab Jas Gripen C-Like Fighter
http://www.iaeme.com/IJMET/index.asp 570 editor@iaeme.com
Figure 2 Structured grid SAAB JAS Gripen C like.
Vortex dynamics analysis was used to analyze the fuselage and RuV effects of the Gripen-
like fighter canard [15]. Vortex dynamics analysis involved flow visualization to analyze
fighters and a review of the measurement results. The flow visualization plot of the primary
vortex center was also presented, which may also generate the second vortex center.
Afterward, the measurement results were analyzed.
3. RESULT AND DISCUSSION
3.1. Performance
Figure 3 Distribution curve of CFD simulation of CL, CD and CL/CD of SAAB JAS Gripen C-like
aircraft
The simulation results in the form of CL, CD, and lifts to drag ratio was shown in Figure 3.
In Figure 3, the CL of a) SAAB JAS Gripen C-like aircraft became higher and b) the
distribution curve of CD simulation of SAAB JAS Gripen C-like aircraft were exposed.
5. Sutrisno, Setyawan Bekti Wibowo, Sigit Iswahyudi and Tri Agung Rohmat
http://www.iaeme.com/IJMET/index.asp 571 editor@iaeme.com
3.2. Streamline simulation on canard and wing at AoA 100
, 200
, 300
and 600
In Figure 4 displayed flow pathline speed of 102,9 m/s at AoA variation 300
and 600
. In the
beginning, swirling flow pathlines described two vortex cores. Figure 4.a described a flow
pathline as well as a picture of the vortex core above the canard on AoA 100
, along with a
picture of the vortex core above the wing.
(a) (b)
(c) (d)
Figure 4 Streamline visualization/ flow pathline above the canard and the wing at AoA a) 100
, b) 200
,
c) 300
and d) 600
.
It appeared that the vortex core above the canard started dragging the vortex core above
the wing. Figure 4.b and c illustrated the vortex cores, above the canard from the canard and
above the wing began to coalesce became one core, gave strong drag on the vortex core in the
leading edge of the wing so that it started to release. In Figure 4.b and c, the rolled-up vortex
from the vortex core in leading edge wing started to release and to weaken, so that the laminar
flow behind it tended to weaken. The appearance in Figure 4.b and c showed the effect of the
slotted leading edge gave rise to a strong vortex core that dragged strong vortex core with the
direction getting stronger but tend to escape after the leading edge.
3.3. Limiting streamline on the aircraft surface above the wing at AoA 300
and
600
.
In Figure 5.a and b one could see the wall-shear-streamlines above the wing at AoA 300
and
600
. In Figure 5.a one could see the limiting streamline above canard flows laminar, as a result
of the flow path line in Figure 5.a flow over the canard tend to curl out, as well as above the
wing at the end of the leading edge tends to rolled up and behind it tends to laminate curved
out, with the trailing edge tends to be laminar straight backward. Whereas the streamlined
6. Vortex Dynamic Investigation of Wing Slotted Gap of Saab Jas Gripen C-Like Fighter
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effect in Figure 5.b shown at the leading edge of the strong vortex core which tends to begin
to detach behind it, resulting in the rolled-up vortex in the wing leading edge followed by the
laminar flow which tends to curl out solidly, and on the trailing edge the wing tend to
laminate backward.
(a) (b)
Figure 5 Wall shear streamlines above the wing at AoA a) 300
and b) 600
.
3.4. Surface pressure contour at AoA 200
, 300
, 400
, 600
and vortex breakdown
location of the Gripen fighter
Figure 6 displays the wall-pressure distribution above the wing at AoA a) 200
, b) 300
, c) 400
and d) 600
of the SAAB JAS Gripen C-like aircraft
(a) (b)
(c) (d)
Figure 6 Wall-pressure distribution above the wing at AoA a) 100
, b) 200
, c) 300
and d) 600
.
7. Sutrisno, Setyawan Bekti Wibowo, Sigit Iswahyudi and Tri Agung Rohmat
http://www.iaeme.com/IJMET/index.asp 573 editor@iaeme.com
In this study at V = 102.9 m/s, at AoA 400
it measured CL = 1.44. In Figure 6.a above the
canard, it described the negative surface pressure at the leading edge. Moreover, above the
wing, the surface pressure was more negative and reached the negative pressure maximum = -
2.05x104
Pa. Furthermore, as AoA increased, negative surface pressure also increased, as
shown in Figure 6 b) AoA 200
, c) AoA 300
and d) AoA 600
.
The increase in the AoA would result in the vortex breakdown location approaching the
leading edge of the wing as shown in Figure 7. The location of the vortex breakdown is
identified from the ratio of the axial velocity to free velocity (U / U∞) at the value 0.1.
Figure 7 Vortex breakdown location against AoA
3.5. Comparison with previous studies
In the following are shown some of the results of previous studies compared to the results of
the SAAB JAS Gripen C-like aircraft research. Compared to the Sukhoi Su-47 [16], the Su-
47 has a higher lift-to-drag ratio, greater air battle maneuvering capacity, higher range at
subsonic speeds. By the Sukhoi Su-30 research in water tunnel [17], the study emphasized
the increase in the maximum coefficient of lift due to the effect of the aircraft body.
Compared with the results of the Sukhoi Su-30 [14] canard deflection effect of Su-30 was
lifted optimization on high AoA. The maximum CL value of Eurofighter [18], Chengdu J-10
from CFD computation [19] and water tunnel measurement [20] is lower than the Gripen
fighter.
4. CONCLUSION
From the research of SAAB JAS Grip-C-like aircraft, it was found that the slotted leading
edge of the Gripen caused a strong vortex core and therefore additional pointy tip produced
two vortex cores, namely ordinary inner rolled-up vortices in the inner wing leading edge and
outer rolled-up wing leading edge of the slotted gap. Rolled-up vortex cores due to slotted
gaps in the inner rolled-up vortex cores began to coalesce to become one stronger vortex core,
which dragged the inner vortex core in the wing leading edge.
As a result, the CL of SAAB JAS Gripen C-like aircraft became higher. Flow over the
canard tend to curl out, as well as above the wing at the end of the leading edge tends to roll-
up and behind it tends to laminate curved out, with the trailing edge tends to be laminar
0
0.2
0.4
0.6
0.8
1
1.2
0 10 20 30 40 50 60 70 80
(x/C)
Angle of attack (degree)
8. Vortex Dynamic Investigation of Wing Slotted Gap of Saab Jas Gripen C-Like Fighter
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straight backward. As AoA increased, negative surface pressure also increased, and the vortex
breakdown location approaching the leading edge of the wing.
The trend of the vortex core length is getting shorter with the increase of AoA as denoted
by the vortex breakdown location. As the AoA increased, it started to release energy and
weakening and will increase the vortex breakdown location closer to the wing leading edge.
As the AoA increased, the vortex tends to detach in the wing leading edge, resulting
rolled-up vortices in the wing leading edge. On the trailing edge the wing tends to laminarize
backward. The result is a negative surface pressure on the leading edge above the canard and
the wing more negative.
ACKNOWLEDGMENTS
The authors would like to express heartfelt gratitude to Dr. Bramantyo for a fruitful session,
useful suggestions, and collaboration. We appreciate the help of our students Wega, David,
Patricius, and Yogi, and the lab staff members, Ponimin and Wajiono, for giving their help in
construction work and conducting data management, which we gratefully acknowledged. This
study was funded by the Government of the Republic of Indonesia Department of Research
Technology and Higher Education, PTUPT-2018, under the contract 1859/UN1/DITLIT/DIT-
LIT/LT/2018
NOMENCLATURE
vα = angle of attacks (AoA/deg)
y+
= dimensionless wall distance
CL = lift coefficient
CD = drag coefficient
M = Mach number
P = total pressure loss (Pa)
Uc = axial canard vortex centre velocity (m/s)
U∞ = free stream velocity (m/s)
VBD = vortex breakdown location
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