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

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