Application of an Inverse Design Method to the Design of Transonic Nacelles

Abstract

This paper describes the extension and application of a design method to nacelles for turbofan engines under transonic flow conditions. Starting form a generic nacelle shape and a prescribed pressure or Mach number distribution, the inverse design problem for the unknown nacelle geometry is solved. The method uses an existing Euler solver to obtain solutions of the transonic, compressible flow field around the configuration. Examples show that the method os capable of handling axisymmetric and three dimensional flow conditions on isolated and installed nacelles, and that it can be used to design the external as well as the internal surfaces of a nacelle.