System for Transonic Wing Design with Geometric Constraints Based on an Inverse Method

摘要

A computational method is presented for the design of wings with given pressure in transonic flow, in the presence of a fixed body. The method is an inverse method of the residual correction type, combining a 'complex' direct flow solver with 'simple' correction rules. The correction rules make use of simple linear thin wing relations for the subsonic corrections and of a 3D interpretation of the wavy-wall formula for the supersonic corrections. In order to avoid problems with possible nonoptimized configurations, and to fulfill requirements from the structural engineer's point of view, geometric constraints can be taken into account. Weights on these constraints can be adjusted during the iteration process, allowing a flexible control. The practical applicability of the method is demonstrated by an example.