Wind tunnel testing of various designs for flexible, flapping membrane wings.
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Wind tunnel testing of various designs for flexible, flapping membrane wings.

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Published .
Written in English


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A systematic study of membrane wings for flapping flight has been undertaken to assess aerodynamic performance and propulsive efficiency. Many pairs of wings were constructed using nylon fabric or thin Mylar. The wings were placed on a custom built flapping mechanism on a three component sting balance in the wind tunnel. Tests were performed at flapping frequencies from 0 to 4 Hz, at wind speeds from 0 to 6 m/s, and at angles of attack from -5° to +10°. The balance allowed for measurement of lift, thrust/drag, and pitching moment.Aspect ratio and weight behind the spar were found to be important factors in a wing"s performance. It was also found that a crank or rearward bend in the spar can improve performance in certain cases.

The Physical Object
Pagination130 leaves.
Number of Pages130
ID Numbers
Open LibraryOL19216065M
ISBN 100494070846

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Keywords: wind tunnel testing, highly flexible wing, flutter stability. Abstract: The wing was tested from Ma = to Ma = for different angles of attack and stagnation pressures. The static and dynamic behavior of the wing model was monitored and a new High aspect-ratio wings designs . 1) Start the wind tunnel and flap the wings to stable. 2) Take the pictures of the deformed wing in several flapping cycles, and record the loads simultaneously. 3) Stop the wind tunnel and move the model to the next state.   Ornithopter-type MAV depends on its flexible membrane wing structure to initiate passive wing rotation to produce required aerodynamic forces, such as lift and thrust, for hovering and forward flight. 49 In order to produce high performance membrane wing structures, aerodynamic-featured wing profile needs to be inherent in the design of the Cited by: Several technical challenges related to the experimental testing of microflapping wings are resolved in this study: primarily, flapping wings less than 3 in. in length produce loads and.

tested wings in both soaring and flapping flight conditions. Nakata et al [3] studied the flexible flapping wing aerodynamics on an X-wing flapper by combining wind tunnel measurements and a computational method. Wind tunnel measurements were performed to capture the wing deformations and forces generated during the flapping flight. Lift and thrust measurements for compliant flapping wings were obtained with a 3′ × 3′ wind tunnel, a custom-built test stand, and post-processing software [ 26, 27 ]. In all tests, the wind speed was 5 m/s which gave rise to a dynamic pressure of kPa, and the relative angle of attack was 20°.   Test times in a blowdown tunnel or shock tube are much less than in a continuous flow tunnel. NASA wind tunnels are often designated by the cross-sectional dimensions of the test section. The wind tunnel in the lower center of the figure is the NASA Glenn 10 x whose test section is 10 foot high and 10 foot across.   Wind tunnel tests were performed to measure the lift and thrust of the mechanical membrane flapping wing under different frequency, speed, and angle of attack. It is observed that the flexibility of the wing structure will affect the thrust and lift force due to its deformation at high flapping frequency.

New Wing Shape Tested in Wind Tunnel. This thesis is the culmination of research work in developing a parylene MEMS technology to fabricate MEMS wings and large-area parylene actuator skins for real-time adaptive flow control for flapping flight applications. In this thesis, the novel MEMS-based wing technology is presented using titanium-alloy metal (Ti-6AV) as wingframe and parylene-C as wing membrane. WIND TUNNEL MODEL SYSTEMS COMMITTEE The Wind Tunnel Model Systems Committee, as outlined in LAPD , "Boards, Panels, Committees, Councils and Teams", has ownership of this document. All requests for additions, deletions, and changes should be forwarded to the chairman of this committee. This document is uncontrolled when printed. numerical simulation for the rigid and flexible flapping-wings were finally verified by conduct the aerodynamic performance tests in a low turbulence and low Reynolds number wind tunnel. Keywords: Flapping-wing MAV, Flexible Wings, Fluid-Solid Interaction, Wind Tunnel Test 1 INTRODUCTION Flapping-wing micro air vehicle (Flapping-wing.