Experimental analysis of different airfoil in wind tunnel
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I04701072079
International Journal of Computational Engineering Research (IJCER) is dedicated to protecting personal information and will make every reasonable effort to handle collected information appropriately. All information collected, as well as related requests, will be handled as carefully and efficiently as possible in accordance with IJCER standards for integrity and objectivity.
Side force generated by dorsal fin.
The side force generated by a dorsal fin is to make an airplane turn and roll. It is very much effective at high(side slip angle)
ME438 Aerodynamics (week 8)
ME438 Aerodynamics is offered by Dr. Bilal Siddiqui at DHA Suffa University. This lecture set deals with everything about airfoils.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.
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.
IRJET- Design and Fabrication of an Open Circuit Subsonic Wind Tunnel for Edu...
This document describes the design and fabrication of a low-cost subsonic wind tunnel for educational purposes. Key aspects include:
1) The wind tunnel was designed and built by students and a professor to support fluid mechanics experiments at their university on a limited budget.
2) Design considerations included achieving a test section air speed over 10m/s, compact size, ease of use, and longevity.
3) Components like the contraction cone, diffuser, test section, and flow conditioner were designed and fabricated based on guidelines from literature.
4) Experimental testing showed average air speeds in the test section of 12.9m/s, with variations within 1m/s. CFD simulation
Subsonic wind tunnel with animation
This document describes the design and analysis of a small-scale open-loop subsonic wind tunnel and prototype generation. Key aspects include:
- The wind tunnel will be composed of a settling chamber, contraction section, test section, diffuser, and fan to study aerodynamic properties.
- Flow field and drag forces will be measured on 3D printed basic shapes and airfoils, and turbulence intensity will be determined.
- Results from the small-scale wind tunnel are intended to be compatible with practical aerodynamic properties and validate computational fluid dynamics models.
Study of Aircraft Wing with Emphasis on Vibration Characteristics
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.
COMPARISON OF ALUMINUM & COMPOSITE MATERIALS FOR SHIP PROPELLER USING FEA
Ships and underwater vehicles like submarine and torpedoes use propeller for propulsion. In general, propellers are
used to develop significant thrust to propel the vehicle at its operational speed and RPM. The blade geometry and design
are complex involving many controlling parameters. Propeller with conventional isotropic materials creates more vibration
and noise in their operation. It is undesirable in stealth point of view. In the recent years the increased need for
light weight structural element with acoustic insulation has led to the use of fiber reinforced multi layered composite
propeller. The present work is aimed at the static and dynamic analysis of alluminium as well as composite propeller
which is a combination of GFRP (Glass Fiber Reinforced Plastics) and CFRP (Carbon Fiber Reinforced Plastics) materials.
Modeling and analyzing the propeller blade of a underwater vehicle for their strength are carried out in the present
work. A propeller is a complex geometry and requires high end modeling in its software. The solid model of propeller is
developed in CATIA V5 R17. HEXA mesh is generated for the model using HYPERMESH. Static, Eigen and frequency
responses analysis of both alluminium and composite propeller are carried out in ANSYS. Inter laminar shear stresses
are calculated for composite propeller by varying the number of layers. The stresses obtained are well within the limit of
elastic property of the materials. The natural frequencies of composite propeller are found to be higher than that of alluminium
propeller and the harmonic analysis of composite propeller are also better than that of alluminium propeller.
Recommended
I04701072079
International Journal of Computational Engineering Research (IJCER) is dedicated to protecting personal information and will make every reasonable effort to handle collected information appropriately. All information collected, as well as related requests, will be handled as carefully and efficiently as possible in accordance with IJCER standards for integrity and objectivity.
Side force generated by dorsal fin.
The side force generated by a dorsal fin is to make an airplane turn and roll. It is very much effective at high(side slip angle)
ME438 Aerodynamics (week 8)
ME438 Aerodynamics is offered by Dr. Bilal Siddiqui at DHA Suffa University. This lecture set deals with everything about airfoils.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.
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.
IRJET- Design and Fabrication of an Open Circuit Subsonic Wind Tunnel for Edu...
This document describes the design and fabrication of a low-cost subsonic wind tunnel for educational purposes. Key aspects include:
1) The wind tunnel was designed and built by students and a professor to support fluid mechanics experiments at their university on a limited budget.
2) Design considerations included achieving a test section air speed over 10m/s, compact size, ease of use, and longevity.
3) Components like the contraction cone, diffuser, test section, and flow conditioner were designed and fabricated based on guidelines from literature.
4) Experimental testing showed average air speeds in the test section of 12.9m/s, with variations within 1m/s. CFD simulation
Subsonic wind tunnel with animation
This document describes the design and analysis of a small-scale open-loop subsonic wind tunnel and prototype generation. Key aspects include:
- The wind tunnel will be composed of a settling chamber, contraction section, test section, diffuser, and fan to study aerodynamic properties.
- Flow field and drag forces will be measured on 3D printed basic shapes and airfoils, and turbulence intensity will be determined.
- Results from the small-scale wind tunnel are intended to be compatible with practical aerodynamic properties and validate computational fluid dynamics models.
Study of Aircraft Wing with Emphasis on Vibration Characteristics
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.
COMPARISON OF ALUMINUM & COMPOSITE MATERIALS FOR SHIP PROPELLER USING FEA
Ships and underwater vehicles like submarine and torpedoes use propeller for propulsion. In general, propellers are
used to develop significant thrust to propel the vehicle at its operational speed and RPM. The blade geometry and design
are complex involving many controlling parameters. Propeller with conventional isotropic materials creates more vibration
and noise in their operation. It is undesirable in stealth point of view. In the recent years the increased need for
light weight structural element with acoustic insulation has led to the use of fiber reinforced multi layered composite
propeller. The present work is aimed at the static and dynamic analysis of alluminium as well as composite propeller
which is a combination of GFRP (Glass Fiber Reinforced Plastics) and CFRP (Carbon Fiber Reinforced Plastics) materials.
Modeling and analyzing the propeller blade of a underwater vehicle for their strength are carried out in the present
work. A propeller is a complex geometry and requires high end modeling in its software. The solid model of propeller is
developed in CATIA V5 R17. HEXA mesh is generated for the model using HYPERMESH. Static, Eigen and frequency
responses analysis of both alluminium and composite propeller are carried out in ANSYS. Inter laminar shear stresses
are calculated for composite propeller by varying the number of layers. The stresses obtained are well within the limit of
elastic property of the materials. The natural frequencies of composite propeller are found to be higher than that of alluminium
propeller and the harmonic analysis of composite propeller are also better than that of alluminium propeller.
Design and analysis of wing for Unmanned Aerial Vehicle using CFD
Unmanned Aerial Vehicle (UAV) is an important technology for military and security application. Various missions can be done using UAV such as surveillance in unknown areas, forestry conservation, and spying enemy territory. Selection of components such as aerofoil plays huge roll in performers of UAV in terms of lift, drag, load carrying capacity, range etc.
This project presents an approach for designing of wing by selecting proper aerofoil and CFD analysis for verifying aerodynamics characteristics.
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This document discusses numerical analysis of lift and drag performance for a NACA0012 wind turbine airfoil. Two airfoil models were analyzed: one with a regular surface and another with circular dimples added to the upper surface. Computational fluid dynamics software was used to calculate the coefficient of lift and drag at various angles of attack. The results showed that adding dimples to the upper surface increased the lift to drag ratio compared to the regular airfoil surface, indicating improved aerodynamic performance from controlling flow separation with the dimples.
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I am sure after taking this course with proper practice with the material provided in the course the students can execute the Operations as per the industry needs.
Industry methods has been followed while delivering the lectures to provide the industry working environment to the students and all necessary topics has been covered in this course to solve and perform a complete structural problem.
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The document summarizes a computational fluid dynamics study of flow over clean and loaded wings using ANSYS Fluent. It describes simulating flow over an airfoil at angles from 0-20 degrees both with and without a missile model attached. The results show that boundary layer separation begins around 15 degrees for the clean wing and occurs at a lower angle for the loaded wing. However, issues with meshing prevented analysis of the loaded wing case. Increasing angle of attack was found to increase lift forces until stall occurred due to vortex shedding beyond 20 degrees.
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Analysis of wings using Airfoil NACA 4412 at different angle of attack
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.
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This document describes the design, fabrication, and aerodynamic analysis of a radio-controlled aircraft wing. The researchers designed a rectangular wing with a Gottingen 526 airfoil profile using computational fluid dynamics software to analyze lift and drag coefficients. The wing structure and control surfaces were fabricated based on the optimal design parameters. Wind tunnel testing was then used to validate the aerodynamic performance and characteristics of the wing.
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2) The design process involved taking measurements from existing aircraft like the Sukhoi-47, X-29, and Supermarine Spitfire to inform the conceptual and detailed design of the dragonfly aircraft.
3) CFD analysis of the 2D aircraft model showed that the unique dual-wing configuration is capable of producing lift, indicating that the design could potentially fly. The analysis paves the way for future dual-wing aircraft designs.
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Experimental study of aerodynamic characteristics of airfoils using
This document presents an experimental study on modifying airfoil surfaces with dimples of different shapes to observe changes in aerodynamic characteristics. The study will construct models of an NACA 4415 airfoil profile with outward and inward dimples. Wind tunnel experiments will measure coefficients of lift, drag, and moment as well as lift-to-drag ratio. The objective is to see how dimple shapes affect an airfoil's aerodynamic performance. The work plan outlines construction of airfoil models, wind tunnel testing, and data analysis over a period of several weeks.
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Our main aim is to implement the composite materials to the thorp T-211 wing by fabrication of the carbon fiber and aramid fiber by the process of lapping of the sandwich panels.
In the initial stage of manufacturing of the thorp T-211 wing was done with the metals like aluminum. Aluminum has more strength, corrosion resistant and also less weight. So, aluminum has used in all aircraft parts.
But, now the technology has been increased in the material science. So, there is a new material has introduced in the field of materials. That is composite material these materials, Light weight, Resistance to corrosion, High resistance to fatigue damage, reduced machining Tapered sections and compound contours easily accomplished, Can orientate fibers in direction of strength/stiffness needed.
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energy, it is important to develop wind turbine rotor models with high rotation rates and power
coefficients. These elemental forces are summed along the span of the blade to calculate the total forces
and moments exerted on the turbine. This study aimed at manufacturing highly efficient wind turbine
rotor models using NACA profiles.
IEEE Aerospace and Electronic Systems Society as a Graduate Student Member
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Unmanned Aerial Vehicle (UAV) is an important technology for military and security application. Various missions can be done using UAV such as surveillance in unknown areas, forestry conservation, and spying enemy territory. Selection of components such as aerofoil plays huge roll in performers of UAV in terms of lift, drag, load carrying capacity, range etc.
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I am sure after taking this course with proper practice with the material provided in the course the students can execute the Operations as per the industry needs.
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The document summarizes a computational fluid dynamics study of flow over clean and loaded wings using ANSYS Fluent. It describes simulating flow over an airfoil at angles from 0-20 degrees both with and without a missile model attached. The results show that boundary layer separation begins around 15 degrees for the clean wing and occurs at a lower angle for the loaded wing. However, issues with meshing prevented analysis of the loaded wing case. Increasing angle of attack was found to increase lift forces until stall occurred due to vortex shedding beyond 20 degrees.
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- An overview of the contents and sections to be covered in the document, including introduction, history, design process, and conclusions.
- Descriptions of the working principles, basic parts, design considerations and calculations, structural details, and applications of hovercraft.
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Our main aim is to implement the composite materials to the thorp T-211 wing by fabrication of the carbon fiber and aramid fiber by the process of lapping of the sandwich panels.
In the initial stage of manufacturing of the thorp T-211 wing was done with the metals like aluminum. Aluminum has more strength, corrosion resistant and also less weight. So, aluminum has used in all aircraft parts.
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- 1. EXPERIMENTAL ANALYSIS OF DIFFERENT AIRFOILS IN WIND TUNNEL Submitted by: Mahendr Pal (16/201) Mohit Kudal (16/202) Vinay Swami
- 2. Contents Introduction Stages of project Requirement Selected airfoils configuration Application of selected airfoils Challenges Project work processing
- 3. INTRODUCTION AIRFOIL An airfoil is the cross-sectional shape of a wing. An airfoil-shaped body moving through a fluid produces an aerodynamic force. FORCES ON AIRFOIL : Lift Drag
- 4. Fig-Cross-sectional view of wing
- 5. Continued… Wind Tunnel : Wind tunnels are large tubes with air moving inside. The tunnels are used to copy the actions of an object in flight. Researchers use wind tunnel to learn more about how an aircraft will fly.
- 6. STAGES OF PROJECT Choose airfoil for experimental analysis. Choose material for airfoil. Steps for fabrication of airfoil: oPasted balsa wood sheet by using Fevicol. oMarked airfoil boundaries by using airfoil printout page. oWe had given shape of airfoil on balsa wood by cutting through knife. oGave curved shape by rubbing. oDrilling operation was performed at aerodynamic centre of airfoil.
- 7. Continued… Airfoil models tested in subsonic wind tunnel. Collected data of lift and drag. Verified experimental data and available data.
- 8. REQUIREMENTS Young’s Modulus, which shows the resistance of the material against the loads. The more elastic a material is, the more load it can handle. Balsa has lowest density among wood-based material. Density ranges from 40-380 kg/m³
- 9. SELECTED AIRFOILS CONFIGURATION 1. NACA 4412 o Max thickness 12% at 30% chord, o Max camber 4% at 40% chord. o Chord= 27cm. 2. NACA 64A410 o Max thickness 10% at 39.9% chord. o Max camber 2.7% at 50% chord. o Chord = 27cm.
- 10. APPLICATION OF SELECTED AIRFOIL Application of NACA 4412 airfoil: oIt has been generally used in sports plane oThe example includes AAI-AA2 mamba aircraft, aeronca series aircraft like aeronca 65-tac defender, aeronca 11ac chief . Fig- aeronca 11ac chief
- 11. Continued… Application of NACA 64A410 airfoil : oIt has been generally used in heavy bomber aircraft. oThe example includes Dornier Do 317 aircraft which is used during world war 2 by Germany. Fig- Dornier Do 317
- 12. CHALLENGES Cutting challenges by hot wire cutter. Drilling challenge. Selection of hinge material challenge.
- 20. References • Tools, A., 2013. Airfoil tools. Retrieved October, 1, p.2013. • Singh, J., Singh, D.J., Singh, A., Rana, A. and Dahiya, A., 2015. Study of NACA 4412 and Selig 12223 airfoils through computational fluid dynamics. SSRG International Journal of Mechanical Engineering (SSRG-IJME)–volume, 2. • Singer, A., Plotnick, R. and Laflamme, M., 2012. Experimental fluid mechanics of an Ediacaran frond. Palaeontologia Electronica, 15(2), pp.1-14. •Anderson, J.D. and Hunter, L.P., 1987. Introduction to flight. Physics Today, 40, p.125. •Anderson, D., 2001. Understanding flight. FNAL (Fermi National Accelerator Laboratory (FNAL), Batavia, IL (United States)). •Rathakrishnan, E., 2016. Instrumentation, measurements, and experiments in fluids. CRC Press. •Zahari, M.F., 2013. A Study of Drag Force on Different Type of Airfoil in a Subsonic Wind Tunnel (Doctoral dissertation, UMP).
- 21. THANK YOU !