Numerical optimization for airfoil design using special perturbation Techniques. | [Proceedings of 4th International Bhurban Conference on Applied Sciences and Technology • 2005]

Author(s):

1. Zubair Islam: Department of Aerospace Engineering, College of Aeronautical Engineering, NUST, Risalpur, Pakistan

Abstract:

An aerodynamic design method is developed which integrates numerical optimization with flow analysis to determine desired airfoil geometry with improved aerodynamic performance at transonic and supersonic conditions. The flow analysis is based on Euler equations in order to correctly model the phenomenon of transonic and supersonic flows. The optimization method used involves the application of the well established Rosenbrock algorithm. Special perturbation techniques of curve fitting and polynomial shape functions are applied for variation of the airfoil shape. The required objective function to be minimized is wave drag with constraints on the airfoil maximum thickness, along with limitations on the desired lift coefficient and pressure differential. The method is applied to three different airfoils at various transonic and supersonic flow conditions. This study shows that existing supercritical airfoils can be optimized for a given design condition while the drag of conventional symmetrical airfoils can also be reduced over, wide range of transonic and supersonic Mach numbers in a very short time thanks to the special perturbation techniques.

Page(s): 189-197

DOI: DOI not available

Published: Journal: Proceedings of 4th International Bhurban Conference on Applied Sciences and Technology, Volume: 0, Issue: , Year: 2005

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