Design of Supersonic Wings Using an Optimization Strategy Coupled with a Solution Scheme for the Euler Equations.

Abstract

The present paper describes an approach for the design of wings at supersonic speed. It is based on a numerical optimization technique coupled with a solution scheme for the Euler equations. The wings studied here are either conical or three-dimensional delta wings with a straight leading edge. The surface is given by a set of Legendre polynominals. Results of the optimization are shown for conical wings at an onflow Mach number of M &#61 4.8. Here, the design of a wing without a crossflow shock at the upper surface for a relative high lift coefficient is demonstrated. Additionally, the influence of geometrical and aerodynamic parameters on the optimization result is examined. Finally, one example for the design of a three-dimensional wing is given.