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Investigation of self-deploying high-lift effectors applied to membrane wings

Published online by Cambridge University Press:  30 March 2017

N. Osterberg  and
R. Albertani
N. Osterberg
Affiliation:
Oregon State University, Mechanical, Industrial, and Manufacturing Engineering, Corvallis, USA
R. Albertani*
Affiliation:
Oregon State University, Mechanical, Industrial, and Manufacturing Engineering, Corvallis, USA
*
[email protected]
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Abstract

Flow separation followed by aerodynamic stall limits the operation of aircraft. Expanding the flight envelope of aircraft has been a goal of aerodynamicists for decades. This work presents findings from tests in the Oregon State University wind tunnel investigating the effectiveness of a passively actuated suction-surface flap on membrane wings. Experiments were conducted on a rigid plate and membrane wings with and without a pop-up flap. All wings had an aspect ratio of 2, while membrane pre-strain and Reynolds number were varied. An increase in lift at stall was observed for all testing conditions with flap deployment. The observed average increase in maximum lift varied from 5% to 15% for different test conditions. The variation in flap effectiveness is compared to membrane pre-strain, Reynolds number, and wing camber. A quadratic relationship between modelled camber and flap effectiveness is observed, and an optimal level of membrane camber is found to maximise flap effectiveness.

Keywords

Membrane aerofoilpliant wingpop-up flapfeather flaphigh-lift effector
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1239 , May 2017 , pp. 660 - 679
Copyright
Copyright © Royal Aeronautical Society 2017 

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