Design method for non-axisymmetric generalized internal conical flowfield based on double 3D curved shock waves

Abstract

To provide ease of integration design of forebody/hypersonic inward turning inlet as well as to extend the domain of option for basic flowfield of the inlet, a design method for axisymmetric basic flowfield with controllable incident/reflected shock wave and certain post reflected shock parameter distribution is developed by using the method of characteristics and optimization algorithm. On this basis, a design method for non-axisymmetric generalized internal conical (NAGIC) basic flowfield is proposed by using the theory of osculating axisymmetric flows to incident and reflected shock wave in parallel. Numerical simulations are performed to verify the design methods. Detailed flow characteristics of NAGIC flowfield with an elliptical entrance that is assigned somewhat arbitrarily are presented. The incident and reflected shock wave geometries are controllable as given. In cross sections, the shock wave geometries are similar to the entrance shape of the inner cone. In osculating planes, the incident and reflected shock waves attach accurately to the lip and the shoulder, respectively. In addition, the crossflow in the 3D flowfield is negligible, and the flow parameters in the exit plane are almost uniform. Thus, the NAGIC flowfield is suitable for inward turning inlet design with complex configurations.