Numerical Simulations of Low Reynolds Number Flows Around Micro Air Vehicles and Comparison Against Wind Tunnel Data

2006 ◽  
Author(s):  
Vincent Brion ◽  
Motoyuki Aki ◽  
Sergey Shkarayev
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Numerical Simulations ◽  
Low Reynolds Number ◽  
Micro Air Vehicles ◽  
Low Reynolds Number Flows ◽  
Wind Tunnel Data ◽  
Low Reynolds ◽  
Reynolds Number Flows ◽  
Air Vehicles

scholarly journals Design and study of mini wind tunnel for microsystems fluid interaction under low Reynolds number flows

2020 ◽  
Vol 2 (5) ◽  
Author(s):  
K. P. Neriya Hegade ◽  
R. Natalia ◽  
B. Wehba ◽  
A. Mittal ◽  
R. B. Bhat ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Low Reynolds Number ◽  
Low Reynolds Number Flows ◽  
Low Reynolds ◽  
Fluid Interaction ◽  
Reynolds Number Flows

scholarly journals WIND TUNNEL CALIBRATION, CORRECTIONS AND EXPERIMENTAL VALIDATION FOR FIXED-WING MICRO AIR VEHICLES MEASUREMENTS

Aviation ◽  
2020 ◽  
Vol 23 (4) ◽  
pp. 104-113
Author(s):  
Ahmed Aboelezz ◽  
Yunes Elqudsi ◽  
Mostafa Hassanalian ◽  
Ahmed Desoki
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Aspect Ratio ◽  
Low Reynolds Number ◽  
Micro Air Vehicles ◽  
Measured Data ◽  
Published Data ◽  
Low Aspect Ratio ◽  
Low Reynolds ◽  
Air Vehicles

The increase in the number of Unmanned Aerial Vehicles (UAVs) and Micro Air Vehicles (MAVs), which are used in a variety of applications has led to a surge in low Reynolds number aerodynamics research. Flow around fixedwing MAVs has an unusual behavior due to its low aspect ratio and operates at low Reynolds number, which demanded to upgrade the used wind tunnel for this study. This upgrade enables measuring the small aerodynamics forces and moment of fixed-wing MAVs. The wind tunnel used in this work is upgraded with a state of art data acquisition system to deal with the different sensors signals in the wind tunnel. For accurate measurements, the sting balance, angle sensor, and airspeed sensor are calibrated. For validation purposes, an experiment is made on a low aspect ratio flat plate wing at low Reynolds number, and the measured data are corrected and compared with published results. The procedure presented in this paper for the first time gave a detailed and complete guide for upgrading and calibrating old wind tunnel, all the required corrections to correct the measured data was presented, the turbulence level correction new technique presented in this paper could be used to estimate the flow turbulence effect on the measured data and correct the measured data against published data.

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