scholarly journals Aerodynamic and Experimental Analysis of Bio-mimic corrugated dragonfly aerofoil

2020 ◽  
Vol 12 (2) ◽  
pp. 73-85
Author(s):  
Md Akhtar KHAN ◽  
Chinmaya PADHY
Keyword(s):  
Wind Tunnel ◽  
Computational Analysis ◽  
Computational Simulation ◽  
Aerodynamic Characteristics ◽  
Cfd Analysis ◽  
Design Constraints ◽  
Subsonic Wind Tunnel ◽  
Fluent Software ◽  
Icem Cfd ◽  
Pantala Flavescens

In this work, experimental and computational approach is used to understand the corrugation attitude of a bio-inspired dragonfly mimicked corrugated airfoil at low Reynolds number varying from 15000 to 75000 to understand the advantages of pleated corrugated airfoil. The CFD analysis is carried out on the 2-dimensional bio-mimetic corrugated ‘Pantala flavescens’ dragonfly forewing to predict the aerodynamic characteristics of the corrugated dragonfly aerofoil with varying angle of attack from 0° to 8°. The computational analysis of the wing profile is done using the ANSYS-19 ICEM CFD and FLUENT software. For the experimental test, the model is printed in 3-D printer machine and tested in subsonic Wind Tunnel at different speeds and different angle of attacks using a wind tunnel 6-component balance. The computational simulation reveals the exemplary results of the pleated airfoil (corrugated aerofoil) with new design constraints. Finally, the computational result is validated with experimental results.

scholarly journals Determine Aerodynamic Characteristics for FX63-137 Aerofoil by Using Subsonic Wind Tunnel

2014 ◽  
Vol 695 ◽  
pp. 651-654 ◽  
Author(s):  
Magedi Moh M. Saad ◽  
Norzelawati Asmuin
Keyword(s):  
Reynolds Number ◽  
Aluminum Alloy ◽  
Wind Tunnel ◽  
Low Reynolds Number ◽  
Angle Of Attack ◽  
Aerodynamic Characteristics ◽  
Cnc Machine ◽  
Subsonic Wind Tunnel ◽  
Low Reynolds

This paper is primarily concentrated with determining aerodynamic characteristics and choosing the best angle of attack at a maximum lift and low drag for the FX 63-137 aerofoil at a low Reynolds number and a speed of 20m/s and 30m/s, by using subsonic wind tunnel through manufacturing the aerofoil by aluminum alloy using a CNC machine. The proposed methodology is divided into several stages. Firstly, manufacturing the aerofoil using an aluminum alloy. Secondly, the testing process is carried out using subsonic wind tunnel. Thirdly, the results are displayed and compared with results produced from related works, in order to find out the best angle of attack at a maximum lift.

The Effect of Canard to the Aerodynamic Behavior of Blended Wing Body Aircraft

2012 ◽  
Vol 225 ◽  
pp. 38-42
Author(s):  
Zurriati Mohd Ali ◽  
Wahyu Kuntjoro ◽  
Wisnoe Wirachman
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Aerodynamic Characteristic ◽  
Lift Coefficient ◽  
Aerodynamic Characteristics ◽  
Moment Coefficient ◽  
Subsonic Wind Tunnel ◽  
Setting Angle ◽  
Blended Wing Body ◽  
The Moment

This paper presents a study on the effect of canard setting angle on the aerodynamic characteristic of a Blended Wing Body (BWB). Canard effects to BWB aerodynamic characteristics are not widely investigated. Hence the focus of the study is to investigate the variations of lifts, drags and moments when the angles of attack are varied at different canard setting angles. Wind tunnel tests were performed on BWB aircraft with canard setting angles,  ranging from -20˚ to 20˚. Angles of attack,  were varied from -10˚ to 10˚. Aspect ratio and canard planform area were kept fixed. All tests were conducted in the subsonic wind tunnel at Universiti Teknologi MARA, at Mach number of 0.1. The streamlines flow, at the upper surface of the canard was visualized using mini tuft. Result shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The results obtained in this research will be of importance to the understanding of aerodynamic behavior of BWB employing canard in its configuration.

scholarly journals A Detailed Study: CFD Analysis of NACA 0012 at Varying Angles of Attack

2021 ◽  
Vol 9 (VII) ◽  
pp. 2330-2336
Author(s):  
Vani Sadadiwala
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Wind Tunnel ◽  
Computational Analysis ◽  
Cfd Analysis ◽  
Reliable Source ◽  
Relationship Of ◽  
Naca 0012 ◽  
The Relationship ◽  
Symmetric Profile

This work reflects the study and detailed analysis of NACA 0012 airfoil at different angles of attack with a constant value of Reynolds Number. The geometrical designing of the airfoil is done using FreeCad and the computational analysis is carried out using Simflow 4.0- OpenFoam Interface. The analysis is fully based upon the concepts of FEM and CFD. The velocity is kept constant with various angles of attack. CFD methods are reliable source of analysis and hence can be replaced with the experimental wind tunnel methods. Boundary layer approaches were taken into consideration using the meshing techniques. The main purpose of this work is to study the symmetric profile of NACA 0012 with varying angles and the behaviour of 0012 at specific conditions. At the end, various graphs are plotted depicting the relationship of Angle of Attack with other dimensionless quantities.

scholarly journals Experimental Investigations and Computational Analysis on Subsonic Wind Tunnel

2019 ◽  
Vol Volume-3 (Issue-3) ◽  
pp. 1708-1711
Author(s):  
Rishabh Kumar Sahu ◽  
Saurabh Sharma ◽  
Vivek Swaroop | Vishal Kumar ◽  
Keyword(s):  
Wind Tunnel ◽  
Computational Analysis ◽  
Experimental Investigations ◽  
Subsonic Wind Tunnel

Normal Force Computation for Axisymmetric Multistage Launch Vehicle

2013 ◽  
Vol 419 ◽  
pp. 23-29 ◽  
Author(s):  
Laith K. Abbas ◽  
Dong Yang Chen ◽  
Xiao Ting Rui
Keyword(s):  
Computational Analysis ◽  
Normal Force ◽  
Accurate Method ◽  
Launch Vehicle ◽  
Ansys Fluent ◽  
Aerodynamic Loads ◽  
Simulation Purpose ◽  
Fluent Software ◽  
Computational Fluid Dynamics Cfd ◽  
Icem Cfd

The increased demand upon the aeroelastician to obtain the distributed aerodynamic normal force loads for arbitrary launch vehicle configurations necessitated accurate method. In this work, computational fluid dynamics (CFD) is used for the determining the distributed aerodynamic loads of an axisymmetric multistage launch vehicle in the linear angle-of-attack range. ICEM-CFD and ANSYS-FLUENT software are implemented for the meshing and computational analysis. About 2750 iterations were used for the simulation purpose. Computational results are compared to available experimental data. In general, a good result within engineering error margins is obtained.

CFD Analysis of a Low Speed Subsonic Wind Tunnel

2017 ◽  
Author(s):  
Olivio Neto ◽  
Odenir de Almeida
Keyword(s):  
Wind Tunnel ◽  
Cfd Analysis ◽  
Low Speed ◽  
Subsonic Wind Tunnel

scholarly journals A research on aerodynamic characteristics of non-pneumatic tire

2021 ◽  
Vol 22 ◽  
pp. 27
Author(s):  
Hong Li ◽  
Yilun Xu ◽  
Chenlong Si ◽  
Yong Yang
Keyword(s):  
Wind Tunnel ◽  
Structural Parameters ◽  
Wind Tunnel Test ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Coefficient ◽  
Pneumatic Tire ◽  
Simulation Calculation ◽  
Calculation Results ◽  
Fluent Software ◽  
Static Conditions

Application of non-pneumatic tire (NPT) has been increased during the last decade. The aerodynamic characteristics of the wheel with NPT has been studied due to significance on improvement of handling and reduction of fuel consumption. In this paper, first, an original NPT model was simulated by CATIA software, and the influence of NPT structural parameters on aerodynamic characteristics was studied by Fluent software. The simulation calculation results showed that: the reduction of tire width and spoke length, and the increase of spoke thickness can effectively decrease aerodynamic coefficient. Then, the MIRA model was used to study the influence of NPT on aerodynamic characteristics of the whole vehicle under driving conditions. Studies showed that: NPT increased the resistance of the whole vehicle, and 63.1% of the resistance at the wheels was provided by the front wheels. Finally, the wind tunnel test was conducted to study aerodynamic characteristics of the optimized NPT model under static conditions and verify the simulation calculation.

Aerodynamic design and computational analysis of yaw sphere for subsonic wind tunnel

2020 ◽  
Author(s):  
Akhila Rupesh ◽  
J. V. Muruga Lal Jeyan
Keyword(s):  
Wind Tunnel ◽  
Computational Analysis ◽  
Aerodynamic Design ◽  
Subsonic Wind Tunnel

Subsonic Wind Tunnel Testing Handbook

1991 ◽  
Author(s):  
Michael G. Alexander
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Testing ◽  
Subsonic Wind Tunnel ◽  
Tunnel Testing
Sign in / Sign up

Export Citation Format

Share Document