Low Reynolds Number Aerodynamics of Low-Aspect-Ratio, Thin/Flat/Cambered-Plate Wings
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In this paper, the authors measured the lift, drag, and pitching moment about the quarter chord on a series of thin flat plates and cambered plates at chord Reynolds numbers varying between 60,000 and 200,000.Abstract:
The design of micro aerial vehicles requires a better understanding of the aerodynamics of small low-aspect-ratio wings An experimental investigation has focused on measuring the lift, drag, and pitching moment about the quarter chord on a series of thin flat plates and cambered plates at chord Reynolds numbers varying between 60,000 and 200,000 Results show that the cambered plates offer better aerodynamic characteristics and performance It also appears that the trailing-edge geometry of the wings and the turbulence intensity in the wind tunnel do not have a strong effect on the lift and drag for thin wings at low Reynolds numbers Moreover, the results did not show the presence of any hysteresis, which is usually observed with thick airfoils/wingsread more
Citations
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Effect of the angle of attack on the transient lift during the interaction of a vortex with a flat plate. Potential theory and experimental results
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Theoretical Prediction of Roll Moment Due to Sideslip for Thin Low-Aspect-Ratio Wings
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Can Scalable Design of Wings for Flapping Wing Micro Air Vehicle Be Inspired by Natural Flyers
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References
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Book
Fundamentals of Aerodynamics
TL;DR: In this article, Navier-Stokes et al. discuss the fundamental principles of Inviscid, Incompressible Flow over airfoils and their application in nonlinear Supersonic Flow.
Book
Low-Speed Wind Tunnel Testing
William H. Rae,Alan Pope +1 more
TL;DR: The use of wind tunnel data for aerodynamic experiments has been studied in this article, where three dimensions of three-dimensional flow and pressure, flow, and shear stress measurements are used to calibrate the test section.
Journal ArticleDOI
Wind tunnel tests of wings at Reynolds numbers below 70 000
TL;DR: In this article, a planform wing was tested at Reynolds numbers as low as 20 000 in a low turbulence wind tunnel and the best profile was a thin plate with a 5% circular arc camber.