This document describes a study on the design and computational fluid dynamic (CFD) analysis of a spiroid winglet to analyze its effects on aircraft performance. Spiroid winglets are bio-inspired wingtip devices that can reduce lift-induced drag. The study involves modifying an existing spiroid winglet design with a 3600 blended wingtip and conducting CFD simulations to evaluate the aerodynamic performance. The CFD analysis is conducted using commercial software Fluent to simulate airflow around the modified spiroid winglet design. Results are compared to an earlier study to validate the CFD methodology. Preliminary results show the modified spiroid winglet design improves aircraft performance by further reducing wingtip vortices and
Evaluation of Over-speed, Burst Margin and Estimation of Low-cycle Fatigue Li...AM Publications
Aero engine rotor burst evaluation is one of the most important problems to be taken care off, whenever it comes to designing a turbo machinery disc. The consequences of a fiasco can be intense, since the disc disintegrates into multiple pieces and they are hurled away in all the possible direction at high speeds. Due to high thermo-mechanical loading conditions the disc is subjected to varying degrees of temperature from bore to rim. However, the centrifugal force dominates in the disc which ranges from 85%-90% and the rest can be treated as thermal and gas loads. The challenge lies at designing a disc for off design conditions with their varying loads and duty cycles. In present work evaluation of safety margins and low-cycle fatigue (LCF) estimation of an aero engine disc through classical methods and blending the terminologies with simulation engineering to arrive at a probable interpretation of number of duty cycles is carried out. The methodology compares the fatigue parameters involved in evaluation of disc life. The design tool closely connects the flight certification requirement, namely Flight Readiness Certification, Federal Aviation Administration and European Aviation Safety Agency the regulating agencies for safety in air transportation vehicles. Speed regulations through API and MIL handbook for material specification using finite element analysis approach.
Numerical Simulation Over Flat-Disk Aerospike at Mach 6Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
The research paper aims to study the effect of Aerospikes on hypersonic missiles in the reduction of drag and heat flux. Parametric study if the aerospike geometry has been carried out by varying the L/D ratio of the spike. The results have been compared with experimental data at Mach 6. Up to 73.6% decrease in drag is seen at zero angles of attack. The reduction becomes lesser at higher angles of attack. There is a significant increase in pitching moment at an angle of attack and this needs to be further studied. Authors - Vivek Warade (Zeus Numerix), Rahul Pawar and Prof NR Gilke (KJ Somaiya COE)
Optimization of Bolted Joints for Aircraft Engine Using Genetic AlgorithmsIJMER
Genetic Algorithms mimic the evolving technique of nature to better fit populations to a certain environment. Despite this technique has proved its adequacy in several fields, its application in Aerospace is still limited, mostly because of the high quantity of acceptability criteria that the design
must pass and the amount of design parameters. The presented paper explores required GA architecture’s adaptations to be applied in highly restricted systems such as those commonly found in Aerospace applications. The proposed GA was applied to the design of an Aircraft Engine’s Axial Casing bolted joint following static strength restrictions as per FAR 33 regulations. The set of Elitism,
interdependent geometric restrictions, Crossing, and Reproduction modules proved the applicability of
the presented multi-objective GA architecture under 14 restrictions for normal, limit and ultimate loads.
As it is described, the conversion is quickly achieved due to the shortage of the search space; therefore a
modified Variable Crossing per Scheme is proposed to expand the diversity of the genome to compensate
the relatively low impact of the Mutation module. Finally, the process and solutions found were compared against the traditional design process, showing the feasibility of this technique in complex applications in terms of quality of the solution and developing time.
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.
Modeling and analysis of naca 66 206 aerofoil propellereSAT Journals
Abstract
NACA aerofoil shapes have been successfully used over the years as wing and tail sections for general aviation and military aircraft, as well as propellers and helicopter rotors. The aircraft performance is highly affected by induced drag caused by wingtip vortices to improve fuel efficiency. In this research work, the analysis of NACA 66-206 aerofoil propellers was investigated for high-speed aircraft propulsion.CFD analysis is performed on the NACA aerofoil to verify the aerodynamic characteristics and enhancing the lift of the aircraft by changing the orientation of angle of attack 00, 100 and 200 and to determine the drag and lift coefficients by applying inlet velocities. An auxiliary part, winglets are added on propeller blade tip in order to improve the performance of propeller. By adding this auxiliary equipment the weight of propeller are significantly increased. To decrease the weight without compromising the performance of the propeller the fiber reinforced composite materials are used. The effects of stacking sequence layers of composite materials, which were fabricated from Kevlar, carbon, glass fibres, and epoxy resin have been used to increase the strength to weight ratio. To validate the strength of the propeller, Structural and buckling analysis is performed.
Keywords: Aerofoil, Propeller, fiber reinforcement and strength etc…
Optimization is a method of searching of best available value for a given objective function w.r.t constrains. Airplanes always need improvement in their design as part of evolution and survival.
1. The document describes the finite element analysis of a static wing box test rig design. A basic test rig model was created and analyzed in ANSYS Workbench to evaluate stresses and deformations.
2. The initial analysis found deformations up to 0.8mm, exceeding design criteria of 1mm maximum. The model was modified by adding diagonal struts between components to reduce stresses.
3. Analysis of the modified model showed deformations reduced to 0.6mm. A further modification with additional struts reduced the maximum deformation to 0.53mm, demonstrating how design changes can improve structural performance.
FE Based Crash Simulation of Belly Landing of a Light Transport AircraftRSIS International
Crash survivability is one of the key features to be
attended during the design of an airworthy aircraft. Belly/crash
landing is the most common phenomenon to be considered in
developing a crashworthy product. That makes it essential to
have redundant structure to enhance the safety of occupants and
also limit the damage to easily repairable state in case of such
event. Even from the certification point of view, it is necessary to
investigate this event by test/analysis. Recent development of
advance computing and their capability to simulate such
phenomenon to acceptable accuracy under given conditions
conveniently replace the need for test which is otherwise costly.
At the same time, one has to be cautious while selecting the
modeling parameters to simulate the condition near to reality.
Taking advantage of this feature an effort is made to simulate the
belly landing and its consequences on the structure complying to
the guidelines of the federal aviation regulations. This paper
presents the methodology adopted to successfully simulate the
belly landing phenomenon for a light transport aircraft flying
prototype.
Evaluation of Over-speed, Burst Margin and Estimation of Low-cycle Fatigue Li...AM Publications
Aero engine rotor burst evaluation is one of the most important problems to be taken care off, whenever it comes to designing a turbo machinery disc. The consequences of a fiasco can be intense, since the disc disintegrates into multiple pieces and they are hurled away in all the possible direction at high speeds. Due to high thermo-mechanical loading conditions the disc is subjected to varying degrees of temperature from bore to rim. However, the centrifugal force dominates in the disc which ranges from 85%-90% and the rest can be treated as thermal and gas loads. The challenge lies at designing a disc for off design conditions with their varying loads and duty cycles. In present work evaluation of safety margins and low-cycle fatigue (LCF) estimation of an aero engine disc through classical methods and blending the terminologies with simulation engineering to arrive at a probable interpretation of number of duty cycles is carried out. The methodology compares the fatigue parameters involved in evaluation of disc life. The design tool closely connects the flight certification requirement, namely Flight Readiness Certification, Federal Aviation Administration and European Aviation Safety Agency the regulating agencies for safety in air transportation vehicles. Speed regulations through API and MIL handbook for material specification using finite element analysis approach.
Numerical Simulation Over Flat-Disk Aerospike at Mach 6Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
The research paper aims to study the effect of Aerospikes on hypersonic missiles in the reduction of drag and heat flux. Parametric study if the aerospike geometry has been carried out by varying the L/D ratio of the spike. The results have been compared with experimental data at Mach 6. Up to 73.6% decrease in drag is seen at zero angles of attack. The reduction becomes lesser at higher angles of attack. There is a significant increase in pitching moment at an angle of attack and this needs to be further studied. Authors - Vivek Warade (Zeus Numerix), Rahul Pawar and Prof NR Gilke (KJ Somaiya COE)
Optimization of Bolted Joints for Aircraft Engine Using Genetic AlgorithmsIJMER
Genetic Algorithms mimic the evolving technique of nature to better fit populations to a certain environment. Despite this technique has proved its adequacy in several fields, its application in Aerospace is still limited, mostly because of the high quantity of acceptability criteria that the design
must pass and the amount of design parameters. The presented paper explores required GA architecture’s adaptations to be applied in highly restricted systems such as those commonly found in Aerospace applications. The proposed GA was applied to the design of an Aircraft Engine’s Axial Casing bolted joint following static strength restrictions as per FAR 33 regulations. The set of Elitism,
interdependent geometric restrictions, Crossing, and Reproduction modules proved the applicability of
the presented multi-objective GA architecture under 14 restrictions for normal, limit and ultimate loads.
As it is described, the conversion is quickly achieved due to the shortage of the search space; therefore a
modified Variable Crossing per Scheme is proposed to expand the diversity of the genome to compensate
the relatively low impact of the Mutation module. Finally, the process and solutions found were compared against the traditional design process, showing the feasibility of this technique in complex applications in terms of quality of the solution and developing time.
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.
Modeling and analysis of naca 66 206 aerofoil propellereSAT Journals
Abstract
NACA aerofoil shapes have been successfully used over the years as wing and tail sections for general aviation and military aircraft, as well as propellers and helicopter rotors. The aircraft performance is highly affected by induced drag caused by wingtip vortices to improve fuel efficiency. In this research work, the analysis of NACA 66-206 aerofoil propellers was investigated for high-speed aircraft propulsion.CFD analysis is performed on the NACA aerofoil to verify the aerodynamic characteristics and enhancing the lift of the aircraft by changing the orientation of angle of attack 00, 100 and 200 and to determine the drag and lift coefficients by applying inlet velocities. An auxiliary part, winglets are added on propeller blade tip in order to improve the performance of propeller. By adding this auxiliary equipment the weight of propeller are significantly increased. To decrease the weight without compromising the performance of the propeller the fiber reinforced composite materials are used. The effects of stacking sequence layers of composite materials, which were fabricated from Kevlar, carbon, glass fibres, and epoxy resin have been used to increase the strength to weight ratio. To validate the strength of the propeller, Structural and buckling analysis is performed.
Keywords: Aerofoil, Propeller, fiber reinforcement and strength etc…
Optimization is a method of searching of best available value for a given objective function w.r.t constrains. Airplanes always need improvement in their design as part of evolution and survival.
1. The document describes the finite element analysis of a static wing box test rig design. A basic test rig model was created and analyzed in ANSYS Workbench to evaluate stresses and deformations.
2. The initial analysis found deformations up to 0.8mm, exceeding design criteria of 1mm maximum. The model was modified by adding diagonal struts between components to reduce stresses.
3. Analysis of the modified model showed deformations reduced to 0.6mm. A further modification with additional struts reduced the maximum deformation to 0.53mm, demonstrating how design changes can improve structural performance.
FE Based Crash Simulation of Belly Landing of a Light Transport AircraftRSIS International
Crash survivability is one of the key features to be
attended during the design of an airworthy aircraft. Belly/crash
landing is the most common phenomenon to be considered in
developing a crashworthy product. That makes it essential to
have redundant structure to enhance the safety of occupants and
also limit the damage to easily repairable state in case of such
event. Even from the certification point of view, it is necessary to
investigate this event by test/analysis. Recent development of
advance computing and their capability to simulate such
phenomenon to acceptable accuracy under given conditions
conveniently replace the need for test which is otherwise costly.
At the same time, one has to be cautious while selecting the
modeling parameters to simulate the condition near to reality.
Taking advantage of this feature an effort is made to simulate the
belly landing and its consequences on the structure complying to
the guidelines of the federal aviation regulations. This paper
presents the methodology adopted to successfully simulate the
belly landing phenomenon for a light transport aircraft flying
prototype.
IRJET - Design and Computational Fluid Dynamic Simulation of Micro Air Ve...IRJET Journal
This document describes the design and computational fluid dynamic (CFD) simulation of a micro air vehicle (MAV) propeller. It begins with introductions to unmanned aerial vehicles (UAVs) and MAVs. It then discusses propellers for MAVs and the importance of thrust. The document outlines the design of the MAV propeller, including the selection of the Clark-Y airfoil section based on its aerodynamic properties. It also provides the coordinates of the Clark-Y airfoil. Finally, it describes the CFD simulation process using ANSYS Fluent software to analyze thrust performance and validate the analytical results.
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.
Experimental Investigation of Stress Concentration in Cross Section of Crane ...ijtsrd
Crane Hooks are highly liable components and are always subjected to failure due to the amount of stresses concentration which can eventually lead to its failure. To study the stress pattern of crane hook in its loaded condition, a solid model of crane hook is prepared with the help of solid works or Pro E software. Real time pattern of stress concentration in 3D model of crane hook is obtained. By predicting the stress concentration area, the shape of the crane is modified to increase its working life and reduce the failure rates. Hooks are employed in heavy industries to carry tonnes of loads safely. These hooks have a big role to play as far as the safety of the crane loaded is concerned. With more and more industrialization the rate at which these hooks are forged are increasing. This work has been carried out on one of the major crane hook carrying a larger load comparatively. The cad model of the crane hook is initially prepared with the help of existing drawings. It is then followed by implementation of modified cross section of hook in the static structural analysis workbench of ANSYS. The selection was based on the satisfaction of several factors in the form of load carrying capacity, stress induced and deflection Stress analysis plays a significant role in the design of parts and structures that must carry load. In this study, Crane hook which is one of lifting equipment, frequently used in material handling is investigated. Analytical Straight beam, curved beam and Winkler Bach approximation , FEM methods were used by various researchers to study stress pattern of crane hook in its loaded condition. The fatigue of the crane which leads to failure of propagation of cracks by stress concentration. Gabriel. A | Suganth. V | Dr. S. Velumani "Experimental Investigation of Stress Concentration in Cross Section of Crane Hook" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-4 | Issue-6 , October 2020, URL: https://www.ijtsrd.com/papers/ijtsrd33640.pdf Paper Url: https://www.ijtsrd.com/engineering/mechanical-engineering/33640/experimental-investigation-of-stress-concentration-in-cross-section-of-crane-hook/gabriel-a
This document discusses computational fluid dynamics (CFD) analysis and optimization of geometric modifications to the Ahmed body to reduce drag and lift coefficients. The Ahmed body is a simplified bluff body shape used to model important car-like geometry features. The study aims to investigate how modifying parameters like rear slant angle, boat tail angle, and ramp angle can influence aerodynamic performance. CFD simulations are conducted using various turbulence models to analyze velocity contours and pressure distributions around modified geometries. The document reviews several past studies exploring techniques like rear slant angle manipulation, surface roughness elements, trailing edge blowing slots, boat tail configurations, and base bleed outlets for reducing drag on bluff bodies.
The document summarizes the design and testing of the Dynamic Airfoil Testing Apparatus built for the UC Davis Advanced Modeling Aeronautics Team (AMAT). The apparatus allows AMAT to experimentally determine lift and drag coefficients for their airfoil designs in the Atmospheric Boundary-Layer Wind Tunnel. It was designed to measure forces on the airfoil at various angles of attack, collect data during testing, and remain modular, low-cost, and minimally disruptive to airflow. Initial testing produced lift and drag coefficient data for AMAT's double element airfoil across a range of angles of attack.
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 document summarizes a computational fluid dynamics (CFD) simulation of flow around an Ahmed body, which is a simplified vehicle model used to study automotive aerodynamics. The simulation varied the rear slant angle of the Ahmed body from 0 to 40 degrees and analyzed the effects on drag and lift coefficients to determine the optimal angle for minimum drag. Pressure-based solver and k-Epsilon turbulence model were used in the simulation conducted in ANSYS Fluent. The study aimed to better understand drag and lift mechanisms and flow patterns like wake regions behind the vehicle body.
Design and Analysis of Helical Spring in Two Wheeler Suspension System using ...IRJET Journal
This document analyzes the design and finite element analysis of helical springs used in the suspension systems of two-wheel vehicles. It discusses modeling a helical spring for a motorcycle in Creo Parametric and analyzing it in ANSYS for stress and deformation. Three spring profiles - circular, square, and square fillet - are analyzed statically and their stresses and displacements are compared. The results show that the square fillet profile experiences lower stresses and deformations compared to the other profiles, indicating it provides better performance for the suspension system. The study aims to optimize helical spring design through analyzing different profiles using finite element analysis.
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.
Design Evaluation and Optimization of IC Engine Connecting Rods '“ A Reviewijtsrd
Fatigue analysis and Optimization of connecting rod are the modern trend in automotive engineering industry emphasis on many parameters like total deformation, life, factor of safety, stress biaxiality and fatigue sensitivity. The main scope of this work comprises detailed review on various methods and procedures adopted by different researchers in Fatigue analysis of commercially used Engine Connecting rod. The objective of conducting fatigue analysis varies from each other like Weight reduction, Cost reduction, Shape optimization and fatigue life calculation at varying boundary conditions and loads. Fatigue analysis has a very dominant position in product design and development as more than 50% of the products, structural failures are due to fatigue concept only. The review have emphasized the importance of conducting the fatigue analysis of the connecting rod to identity its critical points, fatigue life and factor of safety etc., for its better performance and life period extension. N. Mohammed Raffic | Dr. K. Ganesh Babu | K. N. Arun Kumar"Design Evaluation and Optimization of IC Engine Connecting Rods “ A Review" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-2 | Issue-3 , April 2018, URL: http://www.ijtsrd.com/papers/ijtsrd10814.pdf http://www.ijtsrd.com/engineering/mechanical-engineering/10814/design-evaluation-and-optimization-of-ic-engine-connecting-rods--a-review/n-mohammed-raffic
IRJET- Comparative Study of Buckling and Wind Analysis by Changing Differ...IRJET Journal
This document summarizes a study that analyzed steel roof trusses with different parameters (span, slope, and spacing) using buckling and wind load analysis in ETABS software. The objectives were to determine the most economical and lightweight design. Trusses with shorter spans, steeper slopes, and closer spacing had lower weights, costs, and demand capacity ratios. Buckling analysis produced more conservative column designs than wind analysis. The study aims to provide guidance on optimizing truss design for industries requiring large clear spans.
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 discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
IRJET- Static Analysis of Pulsar Bike Frame Made Up of Aluminum Alloy 6063IRJET Journal
This document summarizes research analyzing the static structural performance of a motorcycle frame made from aluminum alloy 6063, as an alternative to mild steel. Finite element analysis was conducted using ANSYS software to model the frame under various static loads. Experimental testing was also performed on a prototype frame to validate the FEA results. The FEA found the aluminum frame experienced less stress than mild steel under the same loads, with a weight reduction of 34%. Experimental compression and impact testing of aluminum 6063 samples agreed reasonably well with FEA predictions. Therefore, replacing mild steel with aluminum 6063 could improve fuel efficiency without compromising frame strength.
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
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.
1) A prototype twisting wing was developed using shape memory alloy actuators to enable variable wing twist.
2) Benchtop and wind tunnel testing showed that the wing could be twisted up to 10 degrees using a PID controller to precisely control wing twist.
3) Wind tunnel tests measured how lift and drag coefficients varied with angle of attack for different levels of controlled wing twist.
Performance characteristics of a hybrid wing for uaveSAT Journals
Abstract Unmanned aerial vehicles (UAV) have become important in the surveillance sector of various governments. Their adavatage of high end technology and minimal risk of human life has been the major boost with respect to the research associated with UAVs. Over the years, the designing and optimization of the aerodynamics of these vehicles has gained lot of importance owing to the increasing urge to develop UAVs with better stability and endurance at subsonic speeds. Since the aircraft should have various performance characteristics as per the desired aerodyanamic requirements, it has been a challenging task to incorporate these characteristics through the use of a single homogeneous airfoil for the wing. With regard to the above discussion, this work deals with the comparison of performance characteristics of a hybrid wing consiting of two airfoil sections combined into a single wing and those of wings with each of the two homogeneous airfoil sections. The optimal wing dimensions for the surveilence UAV was obtained through MATLAB. Three separate models consiting of the hybrid wing, S1223 and E420 were developed through Solid Edge and imported into Fluent. Later, the wing models were subjected to aerodynamic analysis through the implementation of parameters experienced by the wing during the actual flight. The results obtained were compared in order to draw a conclusion regarding the advantages of using a hybrid wing as against the usage of wings with homogeneous airfoil. Keywords: UAV, Hybrid wing, Eppler 420, Seilig 1223 and Fluent.
This document discusses testing methods for analyzing the bending and torsional behavior of wind turbine blades. It describes testing a wind turbine blade box girder section under bending-torsional loading to better understand the material properties and structural response. The testing apparatus applies bending or torsional loads individually or together to the blade section sample, which is simply supported at its ends. Strain responses are measured to analyze the nonlinear deformation behavior and effects of various parameters on structural performance.
This document summarizes the design and results of a test rig to measure lift force generated by flapping wings. Numerical modeling was used to predict lift values based on wing geometry and motion parameters like frequency and angle of attack. An experimental test rig was designed and built with servo motors in the wings to control twisting instead of relying on flexibility. Force measurements from the rig were taken using a load cell as frequency and angle of attack were varied. Results showed that increasing frequency and angle of attack both increased lift force as expected based on the numerical predictions. The document provides context on bio-inspired flight and reviews other flapping wing projects to inform the design of the test rig.
A Brief Study, Research, Design, Analysis on Multi Section Variable Camber WingIJERA Editor
Minimizing fuel consumption is one of the major concerns in the aviation industry. In the past decade, there
have been many attempts to improve the fuel efficiency of aircraft. One of the methods proposed is to vary the
lift-to-drag ratio of the aircraft in different flight conditions. To achieve this, the wing of the airplane must be
able to change its configuration during flight, corresponding to different flight regimes.In the research presented
in this thesis, the aerodynamic characteristics of a multisection, variable camber wing were investigated. The
model used in this research had a 160mm chord and a 200mm wingspan, with the ribs divided into 4 sections.
Each section was able to rotate approximately 5 degrees without causing significant discontinuity on the wing
surface. Two pneumatic actuators located at the main spar were used to morph the wing through mechanical
linkages. The multi-section variable camber wing model could provide up to 10 percent change in camber from
the baseline configuration, which had a NACA0015 section.The wing was tested in the free-jet wind tunnel at
three different Reynolds numbers: 322000, 48000, and 636000. Static tests were performed to obtain lift and
drag data for different configurations. Two rigid wings in baseline and camber configuration were built and
tested to compare the test data with variable camber wing. The wind tunnel test results indicated that the multisection
variable camber wing provided a higher lift than the rigid wing in both configurations whereas high drag
was also generated on the variable camber wing due to friction drag on the wing skin. The larger drag value
appeared on variable camber wing in baseline configuration than in cambered configuration resulting in lower
lift-to-drag ratio as compared to the baseline rigid wing whereas the variable camber wing in cambered
configuration had higher lift-to-drag ratio than the cambered rigid wing.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
IRJET - Design and Computational Fluid Dynamic Simulation of Micro Air Ve...IRJET Journal
This document describes the design and computational fluid dynamic (CFD) simulation of a micro air vehicle (MAV) propeller. It begins with introductions to unmanned aerial vehicles (UAVs) and MAVs. It then discusses propellers for MAVs and the importance of thrust. The document outlines the design of the MAV propeller, including the selection of the Clark-Y airfoil section based on its aerodynamic properties. It also provides the coordinates of the Clark-Y airfoil. Finally, it describes the CFD simulation process using ANSYS Fluent software to analyze thrust performance and validate the analytical results.
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.
Experimental Investigation of Stress Concentration in Cross Section of Crane ...ijtsrd
Crane Hooks are highly liable components and are always subjected to failure due to the amount of stresses concentration which can eventually lead to its failure. To study the stress pattern of crane hook in its loaded condition, a solid model of crane hook is prepared with the help of solid works or Pro E software. Real time pattern of stress concentration in 3D model of crane hook is obtained. By predicting the stress concentration area, the shape of the crane is modified to increase its working life and reduce the failure rates. Hooks are employed in heavy industries to carry tonnes of loads safely. These hooks have a big role to play as far as the safety of the crane loaded is concerned. With more and more industrialization the rate at which these hooks are forged are increasing. This work has been carried out on one of the major crane hook carrying a larger load comparatively. The cad model of the crane hook is initially prepared with the help of existing drawings. It is then followed by implementation of modified cross section of hook in the static structural analysis workbench of ANSYS. The selection was based on the satisfaction of several factors in the form of load carrying capacity, stress induced and deflection Stress analysis plays a significant role in the design of parts and structures that must carry load. In this study, Crane hook which is one of lifting equipment, frequently used in material handling is investigated. Analytical Straight beam, curved beam and Winkler Bach approximation , FEM methods were used by various researchers to study stress pattern of crane hook in its loaded condition. The fatigue of the crane which leads to failure of propagation of cracks by stress concentration. Gabriel. A | Suganth. V | Dr. S. Velumani "Experimental Investigation of Stress Concentration in Cross Section of Crane Hook" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-4 | Issue-6 , October 2020, URL: https://www.ijtsrd.com/papers/ijtsrd33640.pdf Paper Url: https://www.ijtsrd.com/engineering/mechanical-engineering/33640/experimental-investigation-of-stress-concentration-in-cross-section-of-crane-hook/gabriel-a
This document discusses computational fluid dynamics (CFD) analysis and optimization of geometric modifications to the Ahmed body to reduce drag and lift coefficients. The Ahmed body is a simplified bluff body shape used to model important car-like geometry features. The study aims to investigate how modifying parameters like rear slant angle, boat tail angle, and ramp angle can influence aerodynamic performance. CFD simulations are conducted using various turbulence models to analyze velocity contours and pressure distributions around modified geometries. The document reviews several past studies exploring techniques like rear slant angle manipulation, surface roughness elements, trailing edge blowing slots, boat tail configurations, and base bleed outlets for reducing drag on bluff bodies.
The document summarizes the design and testing of the Dynamic Airfoil Testing Apparatus built for the UC Davis Advanced Modeling Aeronautics Team (AMAT). The apparatus allows AMAT to experimentally determine lift and drag coefficients for their airfoil designs in the Atmospheric Boundary-Layer Wind Tunnel. It was designed to measure forces on the airfoil at various angles of attack, collect data during testing, and remain modular, low-cost, and minimally disruptive to airflow. Initial testing produced lift and drag coefficient data for AMAT's double element airfoil across a range of angles of attack.
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 document summarizes a computational fluid dynamics (CFD) simulation of flow around an Ahmed body, which is a simplified vehicle model used to study automotive aerodynamics. The simulation varied the rear slant angle of the Ahmed body from 0 to 40 degrees and analyzed the effects on drag and lift coefficients to determine the optimal angle for minimum drag. Pressure-based solver and k-Epsilon turbulence model were used in the simulation conducted in ANSYS Fluent. The study aimed to better understand drag and lift mechanisms and flow patterns like wake regions behind the vehicle body.
Design and Analysis of Helical Spring in Two Wheeler Suspension System using ...IRJET Journal
This document analyzes the design and finite element analysis of helical springs used in the suspension systems of two-wheel vehicles. It discusses modeling a helical spring for a motorcycle in Creo Parametric and analyzing it in ANSYS for stress and deformation. Three spring profiles - circular, square, and square fillet - are analyzed statically and their stresses and displacements are compared. The results show that the square fillet profile experiences lower stresses and deformations compared to the other profiles, indicating it provides better performance for the suspension system. The study aims to optimize helical spring design through analyzing different profiles using finite element analysis.
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.
Design Evaluation and Optimization of IC Engine Connecting Rods '“ A Reviewijtsrd
Fatigue analysis and Optimization of connecting rod are the modern trend in automotive engineering industry emphasis on many parameters like total deformation, life, factor of safety, stress biaxiality and fatigue sensitivity. The main scope of this work comprises detailed review on various methods and procedures adopted by different researchers in Fatigue analysis of commercially used Engine Connecting rod. The objective of conducting fatigue analysis varies from each other like Weight reduction, Cost reduction, Shape optimization and fatigue life calculation at varying boundary conditions and loads. Fatigue analysis has a very dominant position in product design and development as more than 50% of the products, structural failures are due to fatigue concept only. The review have emphasized the importance of conducting the fatigue analysis of the connecting rod to identity its critical points, fatigue life and factor of safety etc., for its better performance and life period extension. N. Mohammed Raffic | Dr. K. Ganesh Babu | K. N. Arun Kumar"Design Evaluation and Optimization of IC Engine Connecting Rods “ A Review" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-2 | Issue-3 , April 2018, URL: http://www.ijtsrd.com/papers/ijtsrd10814.pdf http://www.ijtsrd.com/engineering/mechanical-engineering/10814/design-evaluation-and-optimization-of-ic-engine-connecting-rods--a-review/n-mohammed-raffic
IRJET- Comparative Study of Buckling and Wind Analysis by Changing Differ...IRJET Journal
This document summarizes a study that analyzed steel roof trusses with different parameters (span, slope, and spacing) using buckling and wind load analysis in ETABS software. The objectives were to determine the most economical and lightweight design. Trusses with shorter spans, steeper slopes, and closer spacing had lower weights, costs, and demand capacity ratios. Buckling analysis produced more conservative column designs than wind analysis. The study aims to provide guidance on optimizing truss design for industries requiring large clear spans.
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 discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
IRJET- Static Analysis of Pulsar Bike Frame Made Up of Aluminum Alloy 6063IRJET Journal
This document summarizes research analyzing the static structural performance of a motorcycle frame made from aluminum alloy 6063, as an alternative to mild steel. Finite element analysis was conducted using ANSYS software to model the frame under various static loads. Experimental testing was also performed on a prototype frame to validate the FEA results. The FEA found the aluminum frame experienced less stress than mild steel under the same loads, with a weight reduction of 34%. Experimental compression and impact testing of aluminum 6063 samples agreed reasonably well with FEA predictions. Therefore, replacing mild steel with aluminum 6063 could improve fuel efficiency without compromising frame strength.
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
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.
1) A prototype twisting wing was developed using shape memory alloy actuators to enable variable wing twist.
2) Benchtop and wind tunnel testing showed that the wing could be twisted up to 10 degrees using a PID controller to precisely control wing twist.
3) Wind tunnel tests measured how lift and drag coefficients varied with angle of attack for different levels of controlled wing twist.
Performance characteristics of a hybrid wing for uaveSAT Journals
Abstract Unmanned aerial vehicles (UAV) have become important in the surveillance sector of various governments. Their adavatage of high end technology and minimal risk of human life has been the major boost with respect to the research associated with UAVs. Over the years, the designing and optimization of the aerodynamics of these vehicles has gained lot of importance owing to the increasing urge to develop UAVs with better stability and endurance at subsonic speeds. Since the aircraft should have various performance characteristics as per the desired aerodyanamic requirements, it has been a challenging task to incorporate these characteristics through the use of a single homogeneous airfoil for the wing. With regard to the above discussion, this work deals with the comparison of performance characteristics of a hybrid wing consiting of two airfoil sections combined into a single wing and those of wings with each of the two homogeneous airfoil sections. The optimal wing dimensions for the surveilence UAV was obtained through MATLAB. Three separate models consiting of the hybrid wing, S1223 and E420 were developed through Solid Edge and imported into Fluent. Later, the wing models were subjected to aerodynamic analysis through the implementation of parameters experienced by the wing during the actual flight. The results obtained were compared in order to draw a conclusion regarding the advantages of using a hybrid wing as against the usage of wings with homogeneous airfoil. Keywords: UAV, Hybrid wing, Eppler 420, Seilig 1223 and Fluent.
This document discusses testing methods for analyzing the bending and torsional behavior of wind turbine blades. It describes testing a wind turbine blade box girder section under bending-torsional loading to better understand the material properties and structural response. The testing apparatus applies bending or torsional loads individually or together to the blade section sample, which is simply supported at its ends. Strain responses are measured to analyze the nonlinear deformation behavior and effects of various parameters on structural performance.
This document summarizes the design and results of a test rig to measure lift force generated by flapping wings. Numerical modeling was used to predict lift values based on wing geometry and motion parameters like frequency and angle of attack. An experimental test rig was designed and built with servo motors in the wings to control twisting instead of relying on flexibility. Force measurements from the rig were taken using a load cell as frequency and angle of attack were varied. Results showed that increasing frequency and angle of attack both increased lift force as expected based on the numerical predictions. The document provides context on bio-inspired flight and reviews other flapping wing projects to inform the design of the test rig.
A Brief Study, Research, Design, Analysis on Multi Section Variable Camber WingIJERA Editor
Minimizing fuel consumption is one of the major concerns in the aviation industry. In the past decade, there
have been many attempts to improve the fuel efficiency of aircraft. One of the methods proposed is to vary the
lift-to-drag ratio of the aircraft in different flight conditions. To achieve this, the wing of the airplane must be
able to change its configuration during flight, corresponding to different flight regimes.In the research presented
in this thesis, the aerodynamic characteristics of a multisection, variable camber wing were investigated. The
model used in this research had a 160mm chord and a 200mm wingspan, with the ribs divided into 4 sections.
Each section was able to rotate approximately 5 degrees without causing significant discontinuity on the wing
surface. Two pneumatic actuators located at the main spar were used to morph the wing through mechanical
linkages. The multi-section variable camber wing model could provide up to 10 percent change in camber from
the baseline configuration, which had a NACA0015 section.The wing was tested in the free-jet wind tunnel at
three different Reynolds numbers: 322000, 48000, and 636000. Static tests were performed to obtain lift and
drag data for different configurations. Two rigid wings in baseline and camber configuration were built and
tested to compare the test data with variable camber wing. The wind tunnel test results indicated that the multisection
variable camber wing provided a higher lift than the rigid wing in both configurations whereas high drag
was also generated on the variable camber wing due to friction drag on the wing skin. The larger drag value
appeared on variable camber wing in baseline configuration than in cambered configuration resulting in lower
lift-to-drag ratio as compared to the baseline rigid wing whereas the variable camber wing in cambered
configuration had higher lift-to-drag ratio than the cambered rigid wing.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
The document discusses CFD results analyzing the aerodynamic efficiency of an aircraft wing with and without winglets. It finds that attaching a blended winglet increases the wing's velocity by 2.64% and its aerodynamic efficiency (Cl/Cd) by 5.57% compared to a wing without a winglet. CFD analysis was performed on 10 wing designs with different winglet types, and the design with the blended winglet 2 performed best. The aim of the project was to use CFD to analyze wing efficiency changes from adding winglets and identify the most efficient winglet design.
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.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
Bend twist coupling effect on the Performance of the Wing of an Unmanned Aeri...IRJET Journal
This document discusses the design and analysis of a composite wing for an unmanned aerial vehicle (UAV) to minimize weight while maintaining stiffness and strength. Two wing models are created - one with all isotropic materials and one with composite materials. The composite wing is designed with glass-epoxy ribs and carbon-epoxy spars to take advantage of intrinsic bend-twist coupling effects. The wing models are analyzed in ANSYS to compare the performance of composite and isotropic materials. The results show that a composite wing can achieve lower weight without compromising structural performance.
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.
Study of Aircraft Wing with Emphasis on Vibration CharacteristicsIJERA Editor
It is essential that the structural stability of the aircraft wings is a major consideration in the design of the aircraft. Many studies are being carried out for the design of the wings across the globe by the researches to strengthen the aircraft wings for steady and sturdy structures for dynamic conditions. The design of the aircraft wing using NACA standards is been discussed in this work. The wing analysis is carried out by using computer numerical analysis tool, viz., CAD/CAE and CFD. The necessary inputs for carrying out the structural analysis with emphasis on the vibration are obtained by CFD analysis. The deformation of the wing structures are investigated with respect to the standard airflow velocity. The velocity of air at the inlet is taken as 122 m/s (438 km/h), considering service ceiling of 7625 m at moderate temperature. The modal analysis is considered to analyse the wing to determine the natural frequency for vibration characteristics of the wing structure. The study of the effect of the stresses and deformations of the wing structure on the vibration characteristics of the wing is carried out to understand the effect of stress on natural frequency of the aircraft wing structure. Hence it is possible to correlate the effect of wind pressure on the vibration of the wing structure for particular design of the wing (NACA). The CFD results revealed that the pressure on the upper surface of the wing for all the wing section planes (butt planes-BL) is less, about -4.97e3N/mm2, as compared to the pressure on the lower surface, about 1.08e4 N/mm2, which satisfy the theory of lift generation. The pre-stressed modal analysis shows the correlation of the stress, deformation and the corresponding mode of vibration. It is found that the maximum deformation of 17.164 mm is corresponding to the modal frequency of 179.65 Hz which can be considered as design frequency of the wing structure. However the fundamental natural frequency of the wing structure is 10.352 Hz for the deformation of 11.383 mm.
IRJET- Analysing the Performance of Solar Powered Wing (UAV)IRJET Journal
This document analyzes the performance of a solar-powered wing for an unmanned aerial vehicle (UAV) consisting of two different airfoil sections. Computational fluid dynamics (CFD) software is used to model and analyze wings with the Eppler 421 and Selig 1223 airfoils individually and as a combined wing. Results show that the combined wing profile has lift and drag characteristics between the individual airfoils. Specifically, the Selig 1223 airfoil produces higher lift but also higher drag. The combined wing design and CFD analysis indicate that a solar-powered wing could provide long endurance flights for UAVs.
Experimental study of magnus effect over an aircraft wingeSAT Journals
This document describes an experimental study of applying the Magnus effect to an aircraft wing to improve lift. The study proposes using a treadmill-like motion on the upper surface of an airfoil to increase the pressure difference and generate more lift with less drag. A prototype was designed and tested with a symmetrical airfoil, driving rollers on a belt via a motor. Calculations were done to determine belt length and velocity based on motor RPM and gear ratios. The goal was to extend the aerodynamic performance of conventional wings.
Wind energy is a promising energy source. Modern wind power industry officially started in 1979 in Denmark with a
turbine of few KW and its evaluation brought up to now, devices of which rated power is higher than 20 MW.
The size of wind turbine’s massively increased and their design achieved a common standard device: Horizontal axis,
Three blades, Upwind, Pitch controlled blades, Active yaw system.
Design and Finite Element Analysis of Aircraft Wing using Ribs and SparsIRJET Journal
This document describes the design and finite element analysis of an aircraft wing structure using ribs and spars. The wing structure was modeled in PRO-ENGINEER and then analyzed in ANSYS. Static, fatigue, and modal analyses were performed to determine stresses, life, damage, and deformation under different loads and speeds. The analyses showed that a carbon epoxy composite material performed better than aluminum or glass materials, with lower stresses and higher safety factors. In conclusion, the carbon epoxy material was determined to be better suited for aircraft wings.
IRJET- Numerical Analysis of Nose Landing Gear SystemIRJET Journal
This document presents a numerical analysis of the nose landing gear system of an aircraft using finite element analysis. It begins with an abstract that outlines the objective to determine stress behavior and displacement of the nose gear during landing. It then describes the modeling process where the nose gear was modeled in CAD software and imported into finite element analysis software for meshing and application of loads and constraints. Key steps of the finite element analysis are described including discretization, deriving element equations, assembling global equations, applying loads/boundaries, and solving for results. Results of the finite element analysis such as stress contours, displacement contours, and natural frequencies are presented and discussed.
Structural dynamic analysis of bio inspired carbon polyethylene MAV wingsijmech
Flapping wing micro air vehicles (FWMAVs) are small unmanned aircrafts or flying robots which are intended to be used for surveillance, reconnaissance, biochemical sensing, targeting, tracking, etc. To perform such missions, MAVs are required to do some specific operations such as hovering; slow and high speed flying; quick landing and take-off, etc. During flapping motion through surrounding air, wings experience inertial and aerodynamic forces. For making successful flights in such conditions, wings must have properties such as flexibility, strength, low weight, long fatigue life, etc. For producing such properties, wing material plays a crucial
role. Most of the research related to MAVs is based on aerodynamics and controls. Present research is based on materials and structural aspects of flapping wings. Here materials used are carbon fibres for making wing skeleton and polyethylene for wing membrane. The design for
the wing of 113.8 mm length is inspired from giant hummingbird’s wing. The wing sketch was developed in gambit software by taking position data, generated using digitizer, from printed image of hummingbird wing. Developed sketch was printed and used, as a guide, for making the wing skeleton. The polyethylene film with adhesive was laminated on the skeleton at 150 ºC.
Natural frequencies, nature of mode shapes, and damping characteristics of fabricated wings are determined here
CFD-based numerical analysis of the aerodynamic effects of a Taper wing at di...IRJET Journal
This document discusses a numerical analysis of the aerodynamic effects of wings with different taper ratios using computational fluid dynamics (CFD). The study models wings with taper ratios ranging from 0.4 to 0.8 in increments of 0.2. The CFD simulations analyze how changes in taper ratio impact lift, drag, and lift to drag ratio of the wings. Mesh independence tests are conducted to determine the appropriate mesh density for accurate results. The simulations are run at a freestream velocity of 40 m/s, yielding a Reynolds number of approximately 327931. Key findings from changing the taper ratio are discussed and comparisons are made between the aerodynamic characteristics and lift distributions of the different wing configurations.
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.
IRJET - Application of Biomimetics in Design of Vehicles – A ReviewIRJET Journal
The document discusses how biomimetics has been applied to improve vehicle design by taking inspiration from nature. It provides examples of how owl wings helped enhance aircraft lift, the box fish shape influenced a Mercedes car design to reduce drag, and the kingfisher beak optimized train nose shapes. The paper also examines how shark skin inspired ship hull textures to decrease drag by 3.75%. In general, the document reviews how biological solutions found in nature can help engineers solve complex problems like reducing drag and improving efficiency in vehicles.
The document summarizes the design of L.A.S.E.R. 5, a solar-powered unmanned aerial vehicle (UAV) being constructed by students. The goals are to break the world record for longest straight-line distance by a solar-powered UAV and to safely charge the onboard battery using solar panels and hydrogen fuel cells. The design process involves conceptual optimization under FAI regulations, aerodynamic and structural analysis using software, and selection of an efficient airfoil for long-range gliding performance at low speeds. The composite sailplane design incorporates lessons from previous L.A.S.E.R. iterations to advance renewable energy applications for aircraft.
DESIGN AND ANALYSIS OF AN ACTIVE TWIST ROTOR BLADES WITH D-SPAR MODEL USING C...AM Publications
Today’s helicopters are the result of collaborative work in mechanical engineering and aeronautics. A helicopter main rotor or rotor system is the combination of a rotary wing and a control system that generates the aerodynamic lift force that supports the weight of the helicopter, and the thrust that counteracts aerodynamic drag in forward flight. In the field of rotorcraft, the research in this project is currently focusing on active blade systems to adapt the aerodynamic properties of the blade to the local aerodynamic conditions. Fuel-efficiency, reduction of vibration and noise and increase of the helicopter maximum speed are the benefits expected from these new technologies. A helicopter's rotor is generally made of two or more rotor blades. Rotor blades are made out of various materials, including aluminum, composite structure, and steel or titanium, with abrasion shields along the leading edge. The blade pitch is typically controlled by a swash plate connected to the helicopter flight controls. An Active Twist Rotor (ATR) is developed for future implementation of the individual blade control for vibration and noise reduction in helicopters. The rotor blade is integrally twisted by direct strain actuation using active fiber composites (AFC). In this thesis, the model of rotor blade is designed and analyzed. 3D models are done in CATIA. Analysis is done in Ansys. The materials used for original model are steel and Aluminum alloy, The modified model is analyzed by specifying aluminum alloy using solid element and also the shell element. The optimization results have been obtained for design solutions, connected with the application of active materials.
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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.
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.
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.
Harnessing WebAssembly for Real-time Stateless Streaming PipelinesChristina Lin
Traditionally, dealing with real-time data pipelines has involved significant overhead, even for straightforward tasks like data transformation or masking. However, in this talk, we’ll venture into the dynamic realm of WebAssembly (WASM) and discover how it can revolutionize the creation of stateless streaming pipelines within a Kafka (Redpanda) broker. These pipelines are adept at managing low-latency, high-data-volume scenarios.
International Conference on NLP, Artificial Intelligence, Machine Learning an...gerogepatton
International Conference on NLP, Artificial Intelligence, Machine Learning and Applications (NLAIM 2024) offers a premier global platform for exchanging insights and findings in the theory, methodology, and applications of NLP, Artificial Intelligence, Machine Learning, and their applications. The conference seeks substantial contributions across all key domains of NLP, Artificial Intelligence, Machine Learning, and their practical applications, aiming to foster both theoretical advancements and real-world implementations. With a focus on facilitating collaboration between researchers and practitioners from academia and industry, the conference serves as a nexus for sharing the latest developments in the field.
Optimizing Gradle Builds - Gradle DPE Tour Berlin 2024Sinan KOZAK
Sinan from the Delivery Hero mobile infrastructure engineering team shares a deep dive into performance acceleration with Gradle build cache optimizations. Sinan shares their journey into solving complex build-cache problems that affect Gradle builds. By understanding the challenges and solutions found in our journey, we aim to demonstrate the possibilities for faster builds. The case study reveals how overlapping outputs and cache misconfigurations led to significant increases in build times, especially as the project scaled up with numerous modules using Paparazzi tests. The journey from diagnosing to defeating cache issues offers invaluable lessons on maintaining cache integrity without sacrificing functionality.
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.
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
TIME DIVISION MULTIPLEXING TECHNIQUE FOR COMMUNICATION SYSTEMHODECEDSIET
Time Division Multiplexing (TDM) is a method of transmitting multiple signals over a single communication channel by dividing the signal into many segments, each having a very short duration of time. These time slots are then allocated to different data streams, allowing multiple signals to share the same transmission medium efficiently. TDM is widely used in telecommunications and data communication systems.
### How TDM Works
1. **Time Slots Allocation**: The core principle of TDM is to assign distinct time slots to each signal. During each time slot, the respective signal is transmitted, and then the process repeats cyclically. For example, if there are four signals to be transmitted, the TDM cycle will divide time into four slots, each assigned to one signal.
2. **Synchronization**: Synchronization is crucial in TDM systems to ensure that the signals are correctly aligned with their respective time slots. Both the transmitter and receiver must be synchronized to avoid any overlap or loss of data. This synchronization is typically maintained by a clock signal that ensures time slots are accurately aligned.
3. **Frame Structure**: TDM data is organized into frames, where each frame consists of a set of time slots. Each frame is repeated at regular intervals, ensuring continuous transmission of data streams. The frame structure helps in managing the data streams and maintaining the synchronization between the transmitter and receiver.
4. **Multiplexer and Demultiplexer**: At the transmitting end, a multiplexer combines multiple input signals into a single composite signal by assigning each signal to a specific time slot. At the receiving end, a demultiplexer separates the composite signal back into individual signals based on their respective time slots.
### Types of TDM
1. **Synchronous TDM**: In synchronous TDM, time slots are pre-assigned to each signal, regardless of whether the signal has data to transmit or not. This can lead to inefficiencies if some time slots remain empty due to the absence of data.
2. **Asynchronous TDM (or Statistical TDM)**: Asynchronous TDM addresses the inefficiencies of synchronous TDM by allocating time slots dynamically based on the presence of data. Time slots are assigned only when there is data to transmit, which optimizes the use of the communication channel.
### Applications of TDM
- **Telecommunications**: TDM is extensively used in telecommunication systems, such as in T1 and E1 lines, where multiple telephone calls are transmitted over a single line by assigning each call to a specific time slot.
- **Digital Audio and Video Broadcasting**: TDM is used in broadcasting systems to transmit multiple audio or video streams over a single channel, ensuring efficient use of bandwidth.
- **Computer Networks**: TDM is used in network protocols and systems to manage the transmission of data from multiple sources over a single network medium.
### Advantages of TDM
- **Efficient Use of Bandwidth**: TDM all
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.
Presentation of IEEE Slovenia CIS (Computational Intelligence Society) Chapte...University of Maribor
Slides from talk presenting:
Aleš Zamuda: Presentation of IEEE Slovenia CIS (Computational Intelligence Society) Chapter and Networking.
Presentation at IcETRAN 2024 session:
"Inter-Society Networking Panel GRSS/MTT-S/CIS
Panel Session: Promoting Connection and Cooperation"
IEEE Slovenia GRSS
IEEE Serbia and Montenegro MTT-S
IEEE Slovenia CIS
11TH INTERNATIONAL CONFERENCE ON ELECTRICAL, ELECTRONIC AND COMPUTING ENGINEERING
3-6 June 2024, Niš, Serbia
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.