Flexible- and Rigid-Wing Micro Air Vehicle: Lift and Drag Comparison

2006 ◽  
Vol 43 (2) ◽  
pp. 572-575 ◽  
Author(s):  
Anthony M. DeLuca ◽  
Mark F. Reeder ◽  
Jacob A. Freeman ◽  
Michael V. Ol
Keyword(s):  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Lift And Drag ◽  
Rigid Wing

Experiments on Rigid Wing Undergoing Hover-Capable Flapping Kinematics at Micro-Air-Vehicle-Scale Reynolds Numbers

AIAA Journal ◽  
2016 ◽  
Vol 54 (4) ◽  
pp. 1145-1157 ◽  
Author(s):  
Moble Benedict ◽  
David Coleman ◽  
David B. Mayo ◽  
Inderjit Chopra
Keyword(s):  
Reynolds Numbers ◽  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Rigid Wing

Design and Analysis of Flapping Wing

2011 ◽  
Vol 110-116 ◽  
pp. 3495-3499
Author(s):  
G.C. Vishnu Kumar ◽  
M. Rahamath Juliyana
Keyword(s):  
Experimental Data ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Flapping Wings ◽  
Visualization Technique ◽  
Aerodynamic Forces ◽  
Flapping Motion ◽  
Smoke Flow ◽  
Air Vehicle ◽  
Lift And Drag

This paper the optimum wing planform for flapping motion is investigated by measuring the lift and drag characteristics. A model is designed with a fixed wing and two flapping wings attached to its trailing edge. Using wind tunnel tests are conducted to study the effect of angle of attack (smoke flow visualization technique). The test comprises of measuring the aerodynamic forces with flapping motion and without it for various flapping frequencies and results are presented. It can be possible to produce a micro air vehicle which is capable of stealthy operations for defence requirements by using these experimental data.

Aerodynamic shape optimisation, wind tunnel measurements and CFD analysis of a MAV wing

2012 ◽  
Vol 116 (1181) ◽  
pp. 685-708 ◽  
Author(s):  
M. R. A. Nabawy ◽  
M. M. ElNomrossy ◽  
M. M. Abdelrahman ◽  
G. M. ElBayoumi
Keyword(s):  
Wind Tunnel ◽  
Stokes Equations ◽  
Turbulence Models ◽  
Reynolds Stress Model ◽  
Micro Air Vehicle ◽  
Shape Optimisation ◽  
Aerodynamic Shape ◽  
Air Vehicle ◽  
Wind Tunnel Measurements ◽  
Lift And Drag

Abstract The aerodynamic shape optimisation of a micro air vehicle (MAV) wing is performed to obtain the basic wing geometrical characteristics which produce the maximum range and endurance requirements. Multhopp’s method based on Prandtl’s classical lifting line theory is used for the determination of the spanwise load distribution required during the optimisation process. The obtained lift and drag characteristics are used for the derivation of the range and endurance equations of an electrically driven micro air vehicle. The optimisation process is based on the modified feasible directions gradient based optimisation algorithm. Results are validated using wind tunnel measurements showing very good agreement. Results are also compared with solutions to the Navier-Stokes equations obtained with ANSYS-CFX finite elements using different turbulence models. These include the k-ε and the shear stress transport (SST) models as well as the Reynolds stress model.

Design and Fabrication of an SU-8 Biomimetic Flapping-wing Micro Air Vehicle by MEMS Technology

ROBOT ◽  
2011 ◽  
Vol 33 (3) ◽  
pp. 366-370 ◽  
Author(s):  
Pengcheng CHI ◽  
Weiping ZHANG ◽  
Wenyuan CHEN ◽  
Hongyi LI ◽  
Kun MENG ◽  
...  
Keyword(s):  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Mems Technology
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