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.
Analysis of wings using Airfoil NACA 4412 at different angle of attackIJMER
This document summarizes wind tunnel testing of the NACA 4412 airfoil at different angles of attack. The testing was conducted to analyze lift and drag forces on the airfoil at varying angles. The results found that lift increases with angle of attack until a maximum is reached, after which drag becomes dominant and stall occurs. Graphs and tables presented in the document compare experimental pressure and friction coefficient data from the wind tunnel tests to computational fluid dynamics simulations using different turbulence models. The models were able to accurately predict flow separation locations and other characteristics.
A comparative flow analysis of naca 6409 and naca 4412 aerofoileSAT Publishing House
This document analyzes and compares the flow properties of two airfoil profiles, the NACA 6409 and NACA 4412, using computational fluid dynamics (CFD) modeling in ANSYS. The analysis examines pressure distribution, lift and drag coefficients at varying angles of attack. The NACA 4412 was found to have better lift-to-drag ratio performance and is more efficient for practical applications compared to the NACA 6409.
- 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.
This document summarizes experiments performed on NACA 4412 airfoils in Cal Poly's low speed wind tunnel. Three experiments were conducted: 1) force balance tests on two finite wings to determine coefficients, 2) pressure measurements on a full-span wing to calculate coefficients, and 3) wake rake tests to determine total drag coefficient. The force balance showed lift coefficient increasing pre-stall and dropping post-stall. Pressure data matched theoretical predictions and a NASA study. Lift was found to increase with angle of attack. The NACA 4412 performed best at low angles of attack, suited for a cruiser aircraft.
Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil A...CrimsonPublishersRDMS
Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil Aerodynamic Performance by Najdat Nashat Abdulla* in Crimson Publishers: Peer Reviewed Material Science Journals
Cfd analysis of rae 2822 supercritical airfoil at transonic mach speedseSAT Journals
This document describes a CFD analysis of a RAE 2822 supercritical airfoil with and without wedge profiles at transonic Mach speeds. The analysis seeks to improve airfoil stability when flow approaches transonic Mach numbers. Key findings include observation of shock wave formation when free stream reaches transonic Mach, and drastic changes in pressure, temperature, and density across shocks. Results show lift is reduced in the transonic regime from Mach 0.7 to 1.4. Lift is higher for airfoils with wedge profiles compared to without, and for higher angles of attack. The airfoil with wedge is more stable at 150 angle of attack, with lift drop at Mach 1.1 versus 0.8 without wedge.
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.
This document describes a computational fluid dynamics (CFD) analysis of flow over NACA airfoils conducted using ANSYS. Three airfoils - NACA 6409, NACA 4412, and NACA 0012 - were analyzed. Pressure and velocity distributions, as well as lift and drag coefficients, were computed for the NACA 6409 and NACA 4412 airfoils. The NACA 4412 airfoil was found to have better lift to drag ratio characteristics, making it more efficient. Additionally, the effect of varying angle of attack on the lift and drag coefficients of the NACA 0012 airfoil was investigated.
Analysis of wings using Airfoil NACA 4412 at different angle of attackIJMER
This document summarizes wind tunnel testing of the NACA 4412 airfoil at different angles of attack. The testing was conducted to analyze lift and drag forces on the airfoil at varying angles. The results found that lift increases with angle of attack until a maximum is reached, after which drag becomes dominant and stall occurs. Graphs and tables presented in the document compare experimental pressure and friction coefficient data from the wind tunnel tests to computational fluid dynamics simulations using different turbulence models. The models were able to accurately predict flow separation locations and other characteristics.
A comparative flow analysis of naca 6409 and naca 4412 aerofoileSAT Publishing House
This document analyzes and compares the flow properties of two airfoil profiles, the NACA 6409 and NACA 4412, using computational fluid dynamics (CFD) modeling in ANSYS. The analysis examines pressure distribution, lift and drag coefficients at varying angles of attack. The NACA 4412 was found to have better lift-to-drag ratio performance and is more efficient for practical applications compared to the NACA 6409.
- 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.
This document summarizes experiments performed on NACA 4412 airfoils in Cal Poly's low speed wind tunnel. Three experiments were conducted: 1) force balance tests on two finite wings to determine coefficients, 2) pressure measurements on a full-span wing to calculate coefficients, and 3) wake rake tests to determine total drag coefficient. The force balance showed lift coefficient increasing pre-stall and dropping post-stall. Pressure data matched theoretical predictions and a NASA study. Lift was found to increase with angle of attack. The NACA 4412 performed best at low angles of attack, suited for a cruiser aircraft.
Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil A...CrimsonPublishersRDMS
Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil Aerodynamic Performance by Najdat Nashat Abdulla* in Crimson Publishers: Peer Reviewed Material Science Journals
Cfd analysis of rae 2822 supercritical airfoil at transonic mach speedseSAT Journals
This document describes a CFD analysis of a RAE 2822 supercritical airfoil with and without wedge profiles at transonic Mach speeds. The analysis seeks to improve airfoil stability when flow approaches transonic Mach numbers. Key findings include observation of shock wave formation when free stream reaches transonic Mach, and drastic changes in pressure, temperature, and density across shocks. Results show lift is reduced in the transonic regime from Mach 0.7 to 1.4. Lift is higher for airfoils with wedge profiles compared to without, and for higher angles of attack. The airfoil with wedge is more stable at 150 angle of attack, with lift drop at Mach 1.1 versus 0.8 without wedge.
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.
This document describes a computational fluid dynamics (CFD) analysis of flow over NACA airfoils conducted using ANSYS. Three airfoils - NACA 6409, NACA 4412, and NACA 0012 - were analyzed. Pressure and velocity distributions, as well as lift and drag coefficients, were computed for the NACA 6409 and NACA 4412 airfoils. The NACA 4412 airfoil was found to have better lift to drag ratio characteristics, making it more efficient. Additionally, the effect of varying angle of attack on the lift and drag coefficients of the NACA 0012 airfoil was investigated.
Naca 2415 finding lift coefficient using cfd, theoretical and javafoileSAT Journals
Abstract In this paper we have studied the experimental characteristic graph of NACA 2415.The experimental graphs were taken from the book, “Theory of wing section” by IRA H. ABBOTT. We used these graphs for the validation of our results. Then we use CFD to simulate the experimental flow conditions and check the results and compare them with the experimental results. We meshed the airfoil in ICEM CFD so that the meshing is very precise. We then calculate the NACA 2415 airfoil’s lift at different angle of attack theoretically and using CFD analysis and compare them with the experimental values. We find the errors between experimental and CFD values as well as experimental and theoretical values. We used another simulation software called Javafoil and used it for comparison. Keywords: Experimental, CFD, Theoretical, Javafoil
Spoiler Analysis and Wind Tunnel ExperimentIJERA Editor
As in today's world the use of petroleum products is increasing, it leads to more pollution and degradation of our
environment. This work will investigate the result of an experimental study carried out to determine the
performance of a car spoiler (inverted aerofoil) and study the pressure difference produced by it and also prove
the transit theory of pressure difference over an aerofoil. It is used widely in formula racing cars. The various
angles of attack and there effects on pressure differences will be measured. The performance parameters are to
be investigated and observed.
Index Terms: W
The document presents a computational fluid dynamics analysis of flow over NACA airfoils using ANSYS Fluent. It describes modeling NACA-4412, NACA-6409, and NACA-0012 airfoils, applying boundary conditions, and analyzing lift, drag, velocity and pressure distributions. The analysis found that NACA-4412 had a higher lift-to-drag ratio than NACA-6409. Additionally, increasing the angle of attack was found to initially increase lift and drag coefficients until a certain point, after which lift decreased while drag continued increasing.
VORTEX DYNAMIC INVESTIGATION OF WING SLOTTED GAP OF SAAB JAS GRIPEN C-LIKE FI...IAEME Publication
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
For Video Lecture of this presentation: https://youtu.be/NAjezfbWh4Y
The topics covered in this session are, drag, categories of drag, drag polar equation and drag polar graph, drag polar derivation, induced drag coefficient.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
Numerical Simulation of the Aerodynamic Performance of a H-type Wind Turbine ...Capvidia NV
Wind Turbine Self Starting CFD Simulation with FlowVision This is a nice example for moving bodies. Moment of inertia of turbine is defined and rotation is induced by aerodynamics forces. Simulation results of rotation speed variation during self-starting are in well agreement with the experimental results.
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.
CFD and EXPERIMENTAL ANALYSIS of VORTEX SHEDDING BEHIND D-SHAPED CYLINDERAM Publications
The flow around bluff bodies is an area of great research of scientists for several years. Vortex shedding is
one of the most challenging phenomenon in turbulent flows. This phenomenon was first studied by Strouhal. Many
researchers have modeled the various objects as cylinders with different cross-sections among which square and
circular cylinders were the most interested sections to study the vortex shedding phenomenon. The Vortex Shedding
frequency depends on different aspects of the flow field such as the end conditions, blockage ratio of the flow passage,
and width to height ratio. This case studies the wave development behind a D-Shaped cylinder, at different Reynolds
numbers, for which we expect a vortex street in the wake of the D-Shaped cylinder, the well known as von Kármán
Street. This body typically serves some vital operational function in aerodynamic. In circular cylinder flow separation
point changes with Reynolds number but in D-Shaped cylinder there is fix flow separation point. So there is more
wake steadiness in D-Shaped cylinder as compared to Circular cylinder and drag reduction because of wake
steadiness.In the present work CFD simulation is carried out for flow past a D-Shaped cylinder to see the wake
behavior. The Reynolds number regime currently studied corresponds to low Reynolds number, laminar and
nominally two-dimensional wake. The fluid domain is a two-dimensional plane with a D-Shaped cylinder of
dimensions B=90mm, H=80mm and L=200mm. CFD calculations of the 2-D flow past the D-Shaped cylinder are
presented and results are validated by comparing with Experimental results of pressure distribution on cylinder
surface. The experimentation is carried out using small open type wind tunnel. The flow visualization is done by
smoke visualization technique. Results are presented for various B/H ratios and Reynolds numbers. The variation of
Strouhal number with Reynolds number is found from the analysis. The focus of the present research is on reducing
the wake unsteadiness.
COMPUTATIONAL FLUID DYNAMIC ANALYSIS OF AIRFOIL NACA0015IAEME Publication
1. The document discusses computational fluid dynamic (CFD) analysis of the NACA 0015 airfoil using ANSYS Fluent software to determine coefficients of lift and drag.
2. The airfoil was analyzed at angles of attack from 0 to 15 degrees. Parameters like coefficient of lift, coefficient of drag, and lift to drag ratio were calculated and plotted against angle of attack.
3. The results showed that coefficient of lift increases with angle of attack initially before stall, while coefficient of drag increases steadily. Stall began around 16 degrees angle of attack.
EXPERIMENTAL and ANALYTICAL ANALYSIS of FLOW PAST D-SHAPED CYLINDERAM Publications
The study of flow past the bluff body is very important in aerodynamics. The D-Shaped cylinder is one of the
bluff bodies which serve some vital operational function in aerodynamic. So it is necessary to study the flow past the DShaped
cylinder. In this paper the flow past D-Shaped cylinder of dimensions B=90mm, H=80mm, and L=200mm is
studied experimentally and analytically. The analytical results are validated with experimental results. The flow
parameter drag co-efficient is calculated for different Reynolds number using Drag co-efficient relation and results of
drag co-efficient are validated with experimental results. Based on the experimental and analytical results, the drag coefficient
of circular cylinder and D-Shaped cylinder are compared. The Strouhal number is calculated using Strouhal
number co-relation for different Reynolds number and results of Strouhal number are validated with previous results
from literature. The experimentation is carried in small open type wind tunnel. The Reynolds number regime currently
studied corresponds to low Reynolds number. The present research involves the calculation of drag co-efficient for DShaped
cylinder. This experiment is based on existing wind tunnel that is already developed. The focus of the present
research is on finding the drag co-efficient both by experimentally and analytically.
This document summarizes a CFD simulation of airfoil flow. It describes setting up the fluid domain as a 2D model of an NACA 2412 airfoil with a chord length of 1m. Various turbulence models are evaluated including SST k-omega, RNG k-epsilon, and Spalart-Allmaras. Flow is simulated as both incompressible and compressible. Results show the lift and drag coefficients at different angles of attack. The NACA 2412 airfoil is found to have greater maximum performance than the NACA 0012. Incompressible flow results are validated against experimental data.
This report is a simulation for a flow over an airfoil "NACA 0009" at Reynolds number equals 1 million for four angles of attack using three different turbulence models and of cause a grid independence solution.
The goal of this study is to apply the knowledge obtained from studying in the university and self-learning in order to solve a specific task of finding the coefficient of drag and lift for the airfoil.
A youtube video made by me explaining how to simulate a flow over an airfoil: https://goo.gl/9VYRFM
Team members:
Ahmed Kamal Shalaby
Ahmed Gaber Ahmed
Esraa Mahmoud Saleh
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.
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.
A Good Effect of Airfoil Design While Keeping Angle of Attack by 6 Degreepaperpublications3
Abstract: Airfoil is a shape of wing or blade of (a propeller, rotor or turbine) by which a fluid generates an aerodynamic force. The component of this force perpendicular to the direction of its speed is called lift force and the component parallel to its speed is called drag forces. Here we see that if we set the angle of attack by 6 degree in fluid NACA0012 we found the aerodynamic forces with suitable positive result our research is totally based on iterations method and based on the help of cfd software.
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.
Analysis of aerodynamic characteristics of a supercritical airfoil for low sp...eSAT Publishing House
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.
This document summarizes finite element analyses performed on a rail crane platform and wind turbine. For the rail crane, static structural analyses were conducted to analyze stress and deformation on wheels under different loading and contact conditions. A thermal analysis determined temperature distribution and additional stresses on wheels over time. For the wind turbine, static loads representing real forces were applied to a blade, and modal and harmonic response analyses examined the structure's natural frequencies and response to vibrational loads.
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.
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.
Naca 2415 finding lift coefficient using cfd, theoretical and javafoileSAT Journals
Abstract In this paper we have studied the experimental characteristic graph of NACA 2415.The experimental graphs were taken from the book, “Theory of wing section” by IRA H. ABBOTT. We used these graphs for the validation of our results. Then we use CFD to simulate the experimental flow conditions and check the results and compare them with the experimental results. We meshed the airfoil in ICEM CFD so that the meshing is very precise. We then calculate the NACA 2415 airfoil’s lift at different angle of attack theoretically and using CFD analysis and compare them with the experimental values. We find the errors between experimental and CFD values as well as experimental and theoretical values. We used another simulation software called Javafoil and used it for comparison. Keywords: Experimental, CFD, Theoretical, Javafoil
Spoiler Analysis and Wind Tunnel ExperimentIJERA Editor
As in today's world the use of petroleum products is increasing, it leads to more pollution and degradation of our
environment. This work will investigate the result of an experimental study carried out to determine the
performance of a car spoiler (inverted aerofoil) and study the pressure difference produced by it and also prove
the transit theory of pressure difference over an aerofoil. It is used widely in formula racing cars. The various
angles of attack and there effects on pressure differences will be measured. The performance parameters are to
be investigated and observed.
Index Terms: W
The document presents a computational fluid dynamics analysis of flow over NACA airfoils using ANSYS Fluent. It describes modeling NACA-4412, NACA-6409, and NACA-0012 airfoils, applying boundary conditions, and analyzing lift, drag, velocity and pressure distributions. The analysis found that NACA-4412 had a higher lift-to-drag ratio than NACA-6409. Additionally, increasing the angle of attack was found to initially increase lift and drag coefficients until a certain point, after which lift decreased while drag continued increasing.
VORTEX DYNAMIC INVESTIGATION OF WING SLOTTED GAP OF SAAB JAS GRIPEN C-LIKE FI...IAEME Publication
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
For Video Lecture of this presentation: https://youtu.be/NAjezfbWh4Y
The topics covered in this session are, drag, categories of drag, drag polar equation and drag polar graph, drag polar derivation, induced drag coefficient.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
Numerical Simulation of the Aerodynamic Performance of a H-type Wind Turbine ...Capvidia NV
Wind Turbine Self Starting CFD Simulation with FlowVision This is a nice example for moving bodies. Moment of inertia of turbine is defined and rotation is induced by aerodynamics forces. Simulation results of rotation speed variation during self-starting are in well agreement with the experimental results.
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.
CFD and EXPERIMENTAL ANALYSIS of VORTEX SHEDDING BEHIND D-SHAPED CYLINDERAM Publications
The flow around bluff bodies is an area of great research of scientists for several years. Vortex shedding is
one of the most challenging phenomenon in turbulent flows. This phenomenon was first studied by Strouhal. Many
researchers have modeled the various objects as cylinders with different cross-sections among which square and
circular cylinders were the most interested sections to study the vortex shedding phenomenon. The Vortex Shedding
frequency depends on different aspects of the flow field such as the end conditions, blockage ratio of the flow passage,
and width to height ratio. This case studies the wave development behind a D-Shaped cylinder, at different Reynolds
numbers, for which we expect a vortex street in the wake of the D-Shaped cylinder, the well known as von Kármán
Street. This body typically serves some vital operational function in aerodynamic. In circular cylinder flow separation
point changes with Reynolds number but in D-Shaped cylinder there is fix flow separation point. So there is more
wake steadiness in D-Shaped cylinder as compared to Circular cylinder and drag reduction because of wake
steadiness.In the present work CFD simulation is carried out for flow past a D-Shaped cylinder to see the wake
behavior. The Reynolds number regime currently studied corresponds to low Reynolds number, laminar and
nominally two-dimensional wake. The fluid domain is a two-dimensional plane with a D-Shaped cylinder of
dimensions B=90mm, H=80mm and L=200mm. CFD calculations of the 2-D flow past the D-Shaped cylinder are
presented and results are validated by comparing with Experimental results of pressure distribution on cylinder
surface. The experimentation is carried out using small open type wind tunnel. The flow visualization is done by
smoke visualization technique. Results are presented for various B/H ratios and Reynolds numbers. The variation of
Strouhal number with Reynolds number is found from the analysis. The focus of the present research is on reducing
the wake unsteadiness.
COMPUTATIONAL FLUID DYNAMIC ANALYSIS OF AIRFOIL NACA0015IAEME Publication
1. The document discusses computational fluid dynamic (CFD) analysis of the NACA 0015 airfoil using ANSYS Fluent software to determine coefficients of lift and drag.
2. The airfoil was analyzed at angles of attack from 0 to 15 degrees. Parameters like coefficient of lift, coefficient of drag, and lift to drag ratio were calculated and plotted against angle of attack.
3. The results showed that coefficient of lift increases with angle of attack initially before stall, while coefficient of drag increases steadily. Stall began around 16 degrees angle of attack.
EXPERIMENTAL and ANALYTICAL ANALYSIS of FLOW PAST D-SHAPED CYLINDERAM Publications
The study of flow past the bluff body is very important in aerodynamics. The D-Shaped cylinder is one of the
bluff bodies which serve some vital operational function in aerodynamic. So it is necessary to study the flow past the DShaped
cylinder. In this paper the flow past D-Shaped cylinder of dimensions B=90mm, H=80mm, and L=200mm is
studied experimentally and analytically. The analytical results are validated with experimental results. The flow
parameter drag co-efficient is calculated for different Reynolds number using Drag co-efficient relation and results of
drag co-efficient are validated with experimental results. Based on the experimental and analytical results, the drag coefficient
of circular cylinder and D-Shaped cylinder are compared. The Strouhal number is calculated using Strouhal
number co-relation for different Reynolds number and results of Strouhal number are validated with previous results
from literature. The experimentation is carried in small open type wind tunnel. The Reynolds number regime currently
studied corresponds to low Reynolds number. The present research involves the calculation of drag co-efficient for DShaped
cylinder. This experiment is based on existing wind tunnel that is already developed. The focus of the present
research is on finding the drag co-efficient both by experimentally and analytically.
This document summarizes a CFD simulation of airfoil flow. It describes setting up the fluid domain as a 2D model of an NACA 2412 airfoil with a chord length of 1m. Various turbulence models are evaluated including SST k-omega, RNG k-epsilon, and Spalart-Allmaras. Flow is simulated as both incompressible and compressible. Results show the lift and drag coefficients at different angles of attack. The NACA 2412 airfoil is found to have greater maximum performance than the NACA 0012. Incompressible flow results are validated against experimental data.
This report is a simulation for a flow over an airfoil "NACA 0009" at Reynolds number equals 1 million for four angles of attack using three different turbulence models and of cause a grid independence solution.
The goal of this study is to apply the knowledge obtained from studying in the university and self-learning in order to solve a specific task of finding the coefficient of drag and lift for the airfoil.
A youtube video made by me explaining how to simulate a flow over an airfoil: https://goo.gl/9VYRFM
Team members:
Ahmed Kamal Shalaby
Ahmed Gaber Ahmed
Esraa Mahmoud Saleh
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.
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.
A Good Effect of Airfoil Design While Keeping Angle of Attack by 6 Degreepaperpublications3
Abstract: Airfoil is a shape of wing or blade of (a propeller, rotor or turbine) by which a fluid generates an aerodynamic force. The component of this force perpendicular to the direction of its speed is called lift force and the component parallel to its speed is called drag forces. Here we see that if we set the angle of attack by 6 degree in fluid NACA0012 we found the aerodynamic forces with suitable positive result our research is totally based on iterations method and based on the help of cfd software.
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.
Analysis of aerodynamic characteristics of a supercritical airfoil for low sp...eSAT Publishing House
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.
This document summarizes finite element analyses performed on a rail crane platform and wind turbine. For the rail crane, static structural analyses were conducted to analyze stress and deformation on wheels under different loading and contact conditions. A thermal analysis determined temperature distribution and additional stresses on wheels over time. For the wind turbine, static loads representing real forces were applied to a blade, and modal and harmonic response analyses examined the structure's natural frequencies and response to vibrational loads.
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.
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.
The document analyzes the aerodynamic performance of a NACA0012 airfoil at various angles of attack using computational fluid dynamics (CFD). The study uses Ansys-Fluent to simulate air flow over the airfoil at angles of 4, 6, 8, and 10 degrees with a Reynolds number of 106. The results show increasing lift and drag coefficients with higher angles of attack. Velocity contours indicate higher speeds over the airfoil's upper surface, while pressure contours show lower pressure. Comparison to experimental data finds good agreement, validating CFD as a method for analyzing airfoil performance.
CFD Analysis for Computing Drag force on Various types of blades for Vertical...IRJET Journal
This document discusses a computational fluid dynamics (CFD) analysis of drag forces on various blade profiles for vertical axis wind turbines (VAWTs). Three blade profiles were analyzed: a conventional airfoil blade (EPPLER863), the EPPLER863 profile with one-fourth of the trailing edge removed, and a Lenz2 type turbine blade profile. The CFD analysis found that the Lenz2 profile generated the maximum drag force of 11.21 Newtons and had the lowest drag coefficient of -7.5, indicating it is the most suitable option for VAWTs in urban areas with typical wind speeds of 6-10 m/s. Modifying the EPPLER863 profile was partially successful
Experimental investigation of stepped aerofoil using propeller test rigeSAT Publishing House
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.
IRJET- CFD Approach of Joukowski Airfoil (T=12%), Comparison of its Aerodynam...IRJET Journal
The document presents a computational fluid dynamics study comparing the aerodynamic performance of NACA0012, NACA4412, and Joukowski (T=12%) airfoils at a Reynolds number of 3 million using the k-ε turbulence model. Graphs of lift and drag coefficients, pressure distributions, and maximum CL/CD ratios show that the NACA4412 airfoil performed best with higher lift, lower drag, and a maximum CL/CD ratio, indicating it may be better suited than the other airfoils tested for aerodynamic applications. The study also found the Joukowski airfoil results were similar to the NACA
A Study of Wind Turbine Blade Power Enhancement Using Aerodynamic Properties IJMER
Technological advancements have improvised them over time. In this paper we shall glance at
the features. Wind energy is the most popular renewable energy. In order to increase the use of wind
energy, it is important to develop wind turbine rotor models with high rotation rates and power
coefficients. These elemental forces are summed along the span of the blade to calculate the total forces
and moments exerted on the turbine. This study aimed at manufacturing highly efficient wind turbine
rotor models using NACA profiles.
Numerical investigation of fluid flow and aerodynamic performance on a 2D NAC...editorijrei
The performance of an aircraft wing mostly depends on the aerodynamic characteristics i.e. lift force, drag force, pressure distribution, the ratio of lift to drag etc. In this paper, the influence of aerodynamic performance on two dimensional NACA 4412 airfoil is investigated. The computational method consist of steady state, incompressible, finite volume method, spalart-allmaras turbulence model. The flow has been studied with the help of Navier-Stroke and continuity equations. Numerical simulations were performed at Reynolds number (1x106, 2x106, 3x106, and 4x106) at a different angle of attack (00, 30,60, and 90). The results give the satisfactory measure of confidence of fidelity of the simulation. Aerodynamic forces are calculated with different Reynolds number and angle of attack, after analyzing the data it is found that the higher lift coefficient was obtain in Re-4x106 at an angle of attack 9 whereas low drag coefficient obtained in Re-1x106 at AOA-0.
1) The document summarizes a simulation of air flow over an airfoil (NACA 0010-35) at various angles of attack using computational fluid dynamics (CFD) in ANSYS.
2) The simulation calculates lift and drag coefficients and determines that maximum lift occurs at an angle of 10 degrees, which is considered the stalling point of the airfoil.
3) The simulation also finds that maximum efficiency, defined as the ratio of lift to drag coefficients, occurs at an angle of 1 degree.
The developed y4 copter is an Unmanned Aerial Vehicle with autonomous subsystems which reports the fully automated y4 copter for the first time. Automation is implemented through maintaining the desired roll, pitch and yaw therefore the flight stability as well as in case of controlling elevation. An improved and efficient algorithm that uses Quaternion is implemented to determine Euler angles avoiding Gimbal lock in case of developing an inertial measurement unit. It has a self-stabilization system powered by Proportional
Integral Derivative control system which is computationally affordable by an ordinary 8 bit microcontroller capable of performing only integer operations. A remote is designed to communicate with the y4 copter from the base station using XBee transceiver modules which come with secured communication with long range. The developed system demonstrates simple design offering lower cost and secured means of control.
The developed y4 copter is an Unmanned Aerial Vehicle with autonomous subsystems which reports the
fully automated y4 copter for the first time. Automation is implemented through maintaining the desired
roll, pitch and yaw therefore the flight stability as well as in case of controlling elevation. An improved and
efficient algorithm that uses Quaternion is implemented to determine Euler angles avoiding Gimbal lock in
case of developing an inertial measurement unit. It has a self-stabilization system powered by Proportional
Integral Derivative control system which is computationally affordable by an ordinary 8 bit
microcontroller capable of performing only integer operations. A remote is designed to communicate with
the y4 copter from the base station using XBee transceiver modules which come with secured
communication with long range. The developed system demonstrates simple design offering lower cost and
secured means of control.
Effect of Camber and Angles of Attack on Airfoil CharacteristicsIRJET Journal
This document discusses a study analyzing the effect of camber, position of camber, and angle of attack on the aerodynamic characteristics of airfoils. Sixteen modified asymmetric NACA airfoils were analyzed using computational fluid dynamics (CFD) by varying the camber, camber position, and angle of attack. The results showed the relationship between these parameters and the lift coefficient, drag coefficient, and lift to drag ratio. This provides insight into how changes in airfoil geometry impact aerodynamic 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.
International Journal of Engineering Research and DevelopmentIJERD Editor
Electrical, Electronics and Computer Engineering,
Information Engineering and Technology,
Mechanical, Industrial and Manufacturing Engineering,
Automation and Mechatronics Engineering,
Material and Chemical Engineering,
Civil and Architecture Engineering,
Biotechnology and Bio Engineering,
Environmental Engineering,
Petroleum and Mining Engineering,
Marine and Agriculture engineering,
Aerospace Engineering.
This document discusses determining the aerodynamic characteristics of the FX63-137 airfoil experimentally and through computer simulation. The airfoil was manufactured using a CNC machine and tested in a subsonic wind tunnel at speeds of 20m/s and 30m/s. The results were compared to simulations run using the XFOIL program. The analyses found that the best lift coefficients were 1.677586 at 12 degrees angle of attack for 20m/s wind speed and 1.681103 at 12 degrees for 30m/s, indicating maximum lift for the airfoil is achieved at those conditions.
The International Journal of Mechanical Engineering Research and Technology is an international online journal in English published Quarterly offers a fast publication schedule whilst maintaining rigorous peer review the use of recommended electronic formats for article delivery expedites the process All submitted research articles are subjected to immediate rapid screening by the editors consultation with the Editorial Board or others working in the field as appropriate to ensure they are likely to be the level of interest and importance appropriate for the journal.
Experimental Analysis of a Low Cost Lift and Drag Force Measurement System fo...IRJET Journal
This document describes the experimental analysis of a low-cost lift and drag force measurement system designed for educational wind tunnel experiments. The system uses a mechanical linkage connected to piezoresistive force sensors to measure the lift and drag forces on a NACA 4209 airfoil. The system was tested in a wind tunnel at various air speeds and angles of attack. The experimental coefficient of lift and drag were compared to literature values, finding reasonable accuracy for lift but more error for drag, likely due to sensor fluctuations. The system was also able to indirectly measure wind tunnel air speed with an error of around -6.5% compared to measurements from a differential manometer. Overall, the low-cost system was found to provide sufficiently accurate
To study Magnus Effect on Flettner RotorIRJET Journal
This document discusses using computational fluid dynamics (CFD) software to simulate the Magnus effect on Flettner rotors. It first provides background on Flettner rotors and the Magnus effect. It then describes the methodology, which includes analyzing experimental data on rotating cylinders, establishing relationships between parameters, setting boundary conditions in CFD, running simulations, and validating the results. The simulations model the fluid flow around stationary and rotating cylinders and calculate lift and drag coefficients. The CFD analysis is found to capture the Magnus effect and related fluid phenomena on the rotating cylinders.
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.
Analysis Of Owl-Like Airfoil Aerodynamics At Low Reynolds Number FlowKelly Lipiec
The document analyzes the aerodynamic characteristics of an owl-like airfoil at a low Reynolds number of 23,000 using computational fluid dynamics simulations. It finds that the owl-like airfoil achieves higher lift coefficients and lift-to-drag ratios than the Ishii airfoil, which was designed for high performance at low Reynolds numbers. The owl-like airfoil's round leading edge, flat upper surface, and deeply concaved lower surface contribute to lift enhancement through mechanisms like a suction peak and laminar separation bubble near the leading edge. However, the owl-like airfoil does not achieve its minimum drag coefficient at zero lift, unlike the Ishii airfoil. The document aims to provide insights that can
Similar to IRJET-Subsonic Flow Study and Analysis on Rotating Cylinder Airfoil (20)
TUNNELING IN HIMALAYAS WITH NATM METHOD: A SPECIAL REFERENCES TO SUNGAL TUNNE...IRJET Journal
1) The document discusses the Sungal Tunnel project in Jammu and Kashmir, India, which is being constructed using the New Austrian Tunneling Method (NATM).
2) NATM involves continuous monitoring during construction to adapt to changing ground conditions, and makes extensive use of shotcrete for temporary tunnel support.
3) The methodology section outlines the systematic geotechnical design process for tunnels according to Austrian guidelines, and describes the various steps of NATM tunnel construction including initial and secondary tunnel support.
STUDY THE EFFECT OF RESPONSE REDUCTION FACTOR ON RC FRAMED STRUCTUREIRJET Journal
This study examines the effect of response reduction factors (R factors) on reinforced concrete (RC) framed structures through nonlinear dynamic analysis. Three RC frame models with varying heights (4, 8, and 12 stories) were analyzed in ETABS software under different R factors ranging from 1 to 5. The results showed that displacement increased as the R factor decreased, indicating less linear behavior for lower R factors. Drift also decreased proportionally with increasing R factors from 1 to 5. Shear forces in the frames decreased with higher R factors. In general, R factors of 3 to 5 produced more satisfactory performance with less displacement and drift. The displacement variations between different building heights were consistent at different R factors. This study evaluated how R factors influence
A COMPARATIVE ANALYSIS OF RCC ELEMENT OF SLAB WITH STARK STEEL (HYSD STEEL) A...IRJET Journal
This study compares the use of Stark Steel and TMT Steel as reinforcement materials in a two-way reinforced concrete slab. Mechanical testing is conducted to determine the tensile strength, yield strength, and other properties of each material. A two-way slab design adhering to codes and standards is executed with both materials. The performance is analyzed in terms of deflection, stability under loads, and displacement. Cost analyses accounting for material, durability, maintenance, and life cycle costs are also conducted. The findings provide insights into the economic and structural implications of each material for reinforcement selection and recommendations on the most suitable material based on the analysis.
A Review on the Progress and Challenges of Aluminum-Based Metal Matrix Compos...IRJET Journal
This document reviews the progress and challenges of aluminum-based metal matrix composites (MMCs), focusing on their fabrication processes and applications. It discusses how various aluminum MMCs have been developed using reinforcements like borides, carbides, oxides, and nitrides to improve mechanical and wear properties. These composites have gained prominence for their lightweight, high-strength and corrosion resistance properties. The document also examines recent advancements in fabrication techniques for aluminum MMCs and their growing applications in industries such as aerospace and automotive. However, it notes that challenges remain around issues like improper mixing of reinforcements and reducing reinforcement agglomeration.
Dynamic Urban Transit Optimization: A Graph Neural Network Approach for Real-...IRJET Journal
This document discusses research on using graph neural networks (GNNs) for dynamic optimization of public transportation networks in real-time. GNNs represent transit networks as graphs with nodes as stops and edges as connections. The GNN model aims to optimize networks using real-time data on vehicle locations, arrival times, and passenger loads. This helps increase mobility, decrease traffic, and improve efficiency. The system continuously trains and infers to adapt to changing transit conditions, providing decision support tools. While research has focused on performance, more work is needed on security, socio-economic impacts, contextual generalization of models, continuous learning approaches, and effective real-time visualization.
Structural Analysis and Design of Multi-Storey Symmetric and Asymmetric Shape...IRJET Journal
This document summarizes a research project that aims to compare the structural performance of conventional slab and grid slab systems in multi-story buildings using ETABS software. The study will analyze both symmetric and asymmetric building models under various loading conditions. Parameters like deflections, moments, shears, and stresses will be examined to evaluate the structural effectiveness of each slab type. The results will provide insights into the comparative behavior of conventional and grid slabs to help engineers and architects select appropriate slab systems based on building layouts and design requirements.
A Review of “Seismic Response of RC Structures Having Plan and Vertical Irreg...IRJET Journal
This document summarizes and reviews a research paper on the seismic response of reinforced concrete (RC) structures with plan and vertical irregularities, with and without infill walls. It discusses how infill walls can improve or reduce the seismic performance of RC buildings, depending on factors like wall layout, height distribution, connection to the frame, and relative stiffness of walls and frames. The reviewed research paper analyzes the behavior of infill walls, effects of vertical irregularities, and seismic performance of high-rise structures under linear static and dynamic analysis. It studies response characteristics like story drift, deflection and shear. The document also provides literature on similar research investigating the effects of infill walls, soft stories, plan irregularities, and different
This document provides a review of machine learning techniques used in Advanced Driver Assistance Systems (ADAS). It begins with an abstract that summarizes key applications of machine learning in ADAS, including object detection, recognition, and decision-making. The introduction discusses the integration of machine learning in ADAS and how it is transforming vehicle safety. The literature review then examines several research papers on topics like lightweight deep learning models for object detection and lane detection models using image processing. It concludes by discussing challenges and opportunities in the field, such as improving algorithm robustness and adaptability.
Long Term Trend Analysis of Precipitation and Temperature for Asosa district,...IRJET Journal
The document analyzes temperature and precipitation trends in Asosa District, Benishangul Gumuz Region, Ethiopia from 1993 to 2022 based on data from the local meteorological station. The results show:
1) The average maximum and minimum annual temperatures have generally decreased over time, with maximum temperatures decreasing by a factor of -0.0341 and minimum by -0.0152.
2) Mann-Kendall tests found the decreasing temperature trends to be statistically significant for annual maximum temperatures but not for annual minimum temperatures.
3) Annual precipitation in Asosa District showed a statistically significant increasing trend.
The conclusions recommend development planners account for rising summer precipitation and declining temperatures in
P.E.B. Framed Structure Design and Analysis Using STAAD ProIRJET Journal
This document discusses the design and analysis of pre-engineered building (PEB) framed structures using STAAD Pro software. It provides an overview of PEBs, including that they are designed off-site with building trusses and beams produced in a factory. STAAD Pro is identified as a key tool for modeling, analyzing, and designing PEBs to ensure their performance and safety under various load scenarios. The document outlines modeling structural parts in STAAD Pro, evaluating structural reactions, assigning loads, and following international design codes and standards. In summary, STAAD Pro is used to design and analyze PEB framed structures to ensure safety and code compliance.
A Review on Innovative Fiber Integration for Enhanced Reinforcement of Concre...IRJET Journal
This document provides a review of research on innovative fiber integration methods for reinforcing concrete structures. It discusses studies that have explored using carbon fiber reinforced polymer (CFRP) composites with recycled plastic aggregates to develop more sustainable strengthening techniques. It also examines using ultra-high performance fiber reinforced concrete to improve shear strength in beams. Additional topics covered include the dynamic responses of FRP-strengthened beams under static and impact loads, and the performance of preloaded CFRP-strengthened fiber reinforced concrete beams. The review highlights the potential of fiber composites to enable more sustainable and resilient construction practices.
Survey Paper on Cloud-Based Secured Healthcare SystemIRJET Journal
This document summarizes a survey on securing patient healthcare data in cloud-based systems. It discusses using technologies like facial recognition, smart cards, and cloud computing combined with strong encryption to securely store patient data. The survey found that healthcare professionals believe digitizing patient records and storing them in a centralized cloud system would improve access during emergencies and enable more efficient care compared to paper-based systems. However, ensuring privacy and security of patient data is paramount as healthcare incorporates these digital technologies.
Review on studies and research on widening of existing concrete bridgesIRJET Journal
This document summarizes several studies that have been conducted on widening existing concrete bridges. It describes a study from China that examined load distribution factors for a bridge widened with composite steel-concrete girders. It also outlines challenges and solutions for widening a bridge in the UAE, including replacing bearings and stitching the new and existing structures. Additionally, it discusses two bridge widening projects in New Zealand that involved adding precast beams and stitching to connect structures. Finally, safety measures and challenges for strengthening a historic bridge in Switzerland under live traffic are presented.
React based fullstack edtech web applicationIRJET Journal
The document describes the architecture of an educational technology web application built using the MERN stack. It discusses the frontend developed with ReactJS, backend with NodeJS and ExpressJS, and MongoDB database. The frontend provides dynamic user interfaces, while the backend offers APIs for authentication, course management, and other functions. MongoDB enables flexible data storage. The architecture aims to provide a scalable, responsive platform for online learning.
A Comprehensive Review of Integrating IoT and Blockchain Technologies in the ...IRJET Journal
This paper proposes integrating Internet of Things (IoT) and blockchain technologies to help implement objectives of India's National Education Policy (NEP) in the education sector. The paper discusses how blockchain could be used for secure student data management, credential verification, and decentralized learning platforms. IoT devices could create smart classrooms, automate attendance tracking, and enable real-time monitoring. Blockchain would ensure integrity of exam processes and resource allocation, while smart contracts automate agreements. The paper argues this integration has potential to revolutionize education by making it more secure, transparent and efficient, in alignment with NEP goals. However, challenges like infrastructure needs, data privacy, and collaborative efforts are also discussed.
A REVIEW ON THE PERFORMANCE OF COCONUT FIBRE REINFORCED CONCRETE.IRJET Journal
This document provides a review of research on the performance of coconut fibre reinforced concrete. It summarizes several studies that tested different volume fractions and lengths of coconut fibres in concrete mixtures with varying compressive strengths. The studies found that coconut fibre improved properties like tensile strength, toughness, crack resistance, and spalling resistance compared to plain concrete. Volume fractions of 2-5% and fibre lengths of 20-50mm produced the best results. The document concludes that using a 4-5% volume fraction of coconut fibres 30-40mm in length with M30-M60 grade concrete would provide benefits based on previous research.
Optimizing Business Management Process Workflows: The Dynamic Influence of Mi...IRJET Journal
The document discusses optimizing business management processes through automation using Microsoft Power Automate and artificial intelligence. It provides an overview of Power Automate's key components and features for automating workflows across various apps and services. The document then presents several scenarios applying automation solutions to common business processes like data entry, monitoring, HR, finance, customer support, and more. It estimates the potential time and cost savings from implementing automation for each scenario. Finally, the conclusion emphasizes the transformative impact of AI and automation tools on business processes and the need for ongoing optimization.
Multistoried and Multi Bay Steel Building Frame by using Seismic DesignIRJET Journal
The document describes the seismic design of a G+5 steel building frame located in Roorkee, India according to Indian codes IS 1893-2002 and IS 800. The frame was analyzed using the equivalent static load method and response spectrum method, and its response in terms of displacements and shear forces were compared. Based on the analysis, the frame was designed as a seismic-resistant steel structure according to IS 800:2007. The software STAAD Pro was used for the analysis and design.
Cost Optimization of Construction Using Plastic Waste as a Sustainable Constr...IRJET Journal
This research paper explores using plastic waste as a sustainable and cost-effective construction material. The study focuses on manufacturing pavers and bricks using recycled plastic and partially replacing concrete with plastic alternatives. Initial results found that pavers and bricks made from recycled plastic demonstrate comparable strength and durability to traditional materials while providing environmental and cost benefits. Additionally, preliminary research indicates incorporating plastic waste as a partial concrete replacement significantly reduces construction costs without compromising structural integrity. The outcomes suggest adopting plastic waste in construction can address plastic pollution while optimizing costs, promoting more sustainable building practices.
Solving Linear Differential Equations with Constant CoefficientsIRJET Journal
1) The document discusses methods for finding the solutions to linear differential equations with constant coefficients. It defines such an equation and explains that the complete solution is the combination of the complementary function (C.F.) and particular integral (P.I.).
2) Various methods are presented for determining the C.F. depending on whether the roots of the auxiliary equation are real, imaginary, repeated, etc.
3) Rules are provided for obtaining the P.I. based on the type of function involved (exponential, trigonometric, power, etc.). Examples are worked through to demonstrate the full solution process.
A review on techniques and modelling methodologies used for checking electrom...nooriasukmaningtyas
The proper function of the integrated circuit (IC) in an inhibiting electromagnetic environment has always been a serious concern throughout the decades of revolution in the world of electronics, from disjunct devices to today’s integrated circuit technology, where billions of transistors are combined on a single chip. The automotive industry and smart vehicles in particular, are confronting design issues such as being prone to electromagnetic interference (EMI). Electronic control devices calculate incorrect outputs because of EMI and sensors give misleading values which can prove fatal in case of automotives. In this paper, the authors have non exhaustively tried to review research work concerned with the investigation of EMI in ICs and prediction of this EMI using various modelling methodologies and measurement setups.
Literature Review Basics and Understanding Reference Management.pptxDr Ramhari Poudyal
Three-day training on academic research focuses on analytical tools at United Technical College, supported by the University Grant Commission, Nepal. 24-26 May 2024
Understanding Inductive Bias in Machine LearningSUTEJAS
This presentation explores the concept of inductive bias in machine learning. It explains how algorithms come with built-in assumptions and preferences that guide the learning process. You'll learn about the different types of inductive bias and how they can impact the performance and generalizability of machine learning models.
The presentation also covers the positive and negative aspects of inductive bias, along with strategies for mitigating potential drawbacks. We'll explore examples of how bias manifests in algorithms like neural networks and decision trees.
By understanding inductive bias, you can gain valuable insights into how machine learning models work and make informed decisions when building and deploying them.
Introduction- e - waste – definition - sources of e-waste– hazardous substances in e-waste - effects of e-waste on environment and human health- need for e-waste management– e-waste handling rules - waste minimization techniques for managing e-waste – recycling of e-waste - disposal treatment methods of e- waste – mechanism of extraction of precious metal from leaching solution-global Scenario of E-waste – E-waste in India- case studies.
KuberTENes Birthday Bash Guadalajara - K8sGPT first impressionsVictor Morales
K8sGPT is a tool that analyzes and diagnoses Kubernetes clusters. This presentation was used to share the requirements and dependencies to deploy K8sGPT in a local environment.
A SYSTEMATIC RISK ASSESSMENT APPROACH FOR SECURING THE SMART IRRIGATION SYSTEMSIJNSA Journal
The smart irrigation system represents an innovative approach to optimize water usage in agricultural and landscaping practices. The integration of cutting-edge technologies, including sensors, actuators, and data analysis, empowers this system to provide accurate monitoring and control of irrigation processes by leveraging real-time environmental conditions. The main objective of a smart irrigation system is to optimize water efficiency, minimize expenses, and foster the adoption of sustainable water management methods. This paper conducts a systematic risk assessment by exploring the key components/assets and their functionalities in the smart irrigation system. The crucial role of sensors in gathering data on soil moisture, weather patterns, and plant well-being is emphasized in this system. These sensors enable intelligent decision-making in irrigation scheduling and water distribution, leading to enhanced water efficiency and sustainable water management practices. Actuators enable automated control of irrigation devices, ensuring precise and targeted water delivery to plants. Additionally, the paper addresses the potential threat and vulnerabilities associated with smart irrigation systems. It discusses limitations of the system, such as power constraints and computational capabilities, and calculates the potential security risks. The paper suggests possible risk treatment methods for effective secure system operation. In conclusion, the paper emphasizes the significant benefits of implementing smart irrigation systems, including improved water conservation, increased crop yield, and reduced environmental impact. Additionally, based on the security analysis conducted, the paper recommends the implementation of countermeasures and security approaches to address vulnerabilities and ensure the integrity and reliability of the system. By incorporating these measures, smart irrigation technology can revolutionize water management practices in agriculture, promoting sustainability, resource efficiency, and safeguarding against potential security threats.
CHINA’S GEO-ECONOMIC OUTREACH IN CENTRAL ASIAN COUNTRIES AND FUTURE PROSPECTjpsjournal1
The rivalry between prominent international actors for dominance over Central Asia's hydrocarbon
reserves and the ancient silk trade route, along with China's diplomatic endeavours in the area, has been
referred to as the "New Great Game." This research centres on the power struggle, considering
geopolitical, geostrategic, and geoeconomic variables. Topics including trade, political hegemony, oil
politics, and conventional and nontraditional security are all explored and explained by the researcher.
Using Mackinder's Heartland, Spykman Rimland, and Hegemonic Stability theories, examines China's role
in Central Asia. This study adheres to the empirical epistemological method and has taken care of
objectivity. This study analyze primary and secondary research documents critically to elaborate role of
china’s geo economic outreach in central Asian countries and its future prospect. China is thriving in trade,
pipeline politics, and winning states, according to this study, thanks to important instruments like the
Shanghai Cooperation Organisation and the Belt and Road Economic Initiative. According to this study,
China is seeing significant success in commerce, pipeline politics, and gaining influence on other
governments. This success may be attributed to the effective utilisation of key tools such as the Shanghai
Cooperation Organisation and the Belt and Road Economic Initiative.
Advanced control scheme of doubly fed induction generator for wind turbine us...IJECEIAES
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.