Water tunnel experimental investigation on the aerodynamic performance of flapping wings for nano air vehicles

2011 ◽  
Author(s):  
Krzysztof Sibilski ◽  
Pawel Czekalowski ◽  
Andrzej Gronczewski
Keyword(s):  
Experimental Investigation ◽  
Aerodynamic Performance ◽  
Flapping Wings ◽  
Water Tunnel ◽  
Air Vehicles

scholarly journals Role of Active Morphing in the Aerodynamic Performance of Flapping Wings in Formation Flight

Drones ◽  
2021 ◽  
Vol 5 (3) ◽  
pp. 90
Author(s):  
Ethan Billingsley ◽  
Mehdi Ghommem ◽  
Rui Vasconcellos ◽  
Abdessattar Abdelkefi
Keyword(s):  
Micro Air Vehicles ◽  
Aerodynamic Performance ◽  
Formation Flight ◽  
Optimal Configuration ◽  
Flapping Wings ◽  
Mode Shapes ◽  
Torsional Mode ◽  
Propulsive Efficiency ◽  
Significant Difference ◽  
Air Vehicles

Migratory birds have the ability to save energy during flight by arranging themselves in a V-formation. This arrangement enables an increase in the overall efficiency of the group because the wake vortices shed by each of the birds provide additional lift and thrust to every member. Therefore, the aerodynamic advantages of such a flight arrangement can be exploited in the design process of micro air vehicles. One significant difference when comparing the anatomy of birds to the design of most micro air vehicles is that bird wings are not completely rigid. Birds have the ability to actively morph their wings during the flapping cycle. Given these aspects of avian flight, the objective of this work is to incorporate active bending and torsion into multiple pairs of flapping wings arranged in a V-formation and to investigate their aerodynamic behavior using the unsteady vortex lattice method. To do so, the first two bending and torsional mode shapes of a cantilever beam are considered and the aerodynamic characteristics of morphed wings for a range of V-formation angles, while changing the group size in order to determine the optimal configuration that results in maximum propulsive efficiency, are examined. The aerodynamic simulator incorporating the prescribed morphing is qualitatively verified using experimental data taken from trained kestrel flights. The simulation results demonstrate that coupled bending and twisting of the first mode shape yields the highest propulsive efficiency over a range of formation angles. Furthermore, the optimal configuration in terms of propulsive efficiency is found to be a five-body V-formation incorporating coupled bending and twisting of the first mode at a formation angle of 140 degrees. These results indicate the potential improvement in the aerodynamic performance of the formation flight when introducing active morphing and bioinspiration.

Effect of Skin Flexibility on Aerodynamic Performance of Flexible Skin Flapping Wings for Micro Air Vehicles

2012 ◽  
Vol 39 (1) ◽  
pp. 11-20 ◽  
Author(s):  
H. Yusoff ◽  
M.Z. Abdullah ◽  
M. Abdul Mujeebu ◽  
K.A. Ahmad
Keyword(s):  
Micro Air Vehicles ◽  
Aerodynamic Performance ◽  
Flapping Wings ◽  
Flexible Skin ◽  
Air Vehicles

Bio-Mimetic Millimeter-Scale Flapping Wings for Micro Air Vehicles

2009 ◽  
Author(s):  
Christopher Kroninger ◽  
Jeffrey Pulskamp ◽  
Jessica Bronson ◽  
Ronald G. Polcawich ◽  
Eric Wetzel
Keyword(s):  
Micro Air Vehicles ◽  
Flapping Wings ◽  
Air Vehicles

scholarly journals Experimental Investigation on the Aerodynamic Performance of NLF-0414 Iced-Airfoil

2016 ◽  
Vol 9 (2) ◽  
pp. 587-592 ◽  
Author(s):  
abbas ebrahimi ◽  
majid hajipour ◽  
Hossein Hasheminasa ◽  
◽  
◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Aerodynamic Performance

Aerodynamic Investigation of Double Surface Airfoil

2021 ◽  
Vol 1 (2) ◽  
pp. 41-46
Author(s):  
Siva J ◽  
Suresh C ◽  
Paramaguru V
Keyword(s):  
Experimental Investigation ◽  
Flow Separation ◽  
Research Work ◽  
Aerodynamic Performance ◽  
Aircraft Industry ◽  
Aerodynamic Efficiency ◽  
Flight Vehicles ◽  
Double Surface ◽  
Naca 0012 ◽  
Aerodynamic Investigation

Aircraft industry has been deeply concerned about reduction of drag by reducing flow separation and improving the aerodynamic efficiency of flight vehicles, particularly in commercial and military market by adopting various methods. Reduction of flow separation is a concept by which we can increase aerodynamic efficiency. The purpose of the project is to perform an experimental investigation on aerodynamic performance of NACA 0012 airfoil model with and without splits. It is evident from this research work that the airfoil model with split possesses greater aerodynamic performance by producing lesser overall drag. This is due to the delay in flow separation from the surface.

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