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

Published online by Cambridge University Press:  27 January 2016

M. R. A. Nabawy ,
M. M. ElNomrossy ,
M. M. Abdelrahman  and
G. M. ElBayoumi
M. R. A. Nabawy*
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, The University of Manchester, Manchester, UK Aerospace Engineering Department, Cairo University, Giza, Egypt
M. M. ElNomrossy
Affiliation:
Production, Energy and Automatic Control Department, French University, Cairo, Egypt
M. M. Abdelrahman
Affiliation:
Aerospace Engineering Department, Cairo University, Giza, Egypt
G. M. ElBayoumi
Affiliation:
Aerospace Engineering Department, Cairo University, Giza, Egypt
*
mostafa.ahmednabawy@postgrad.manchester.ac.uk
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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.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1181 , July 2012 , pp. 685 - 708
Copyright
Copyright © Royal Aeronautical Society 2012 

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