Converging-Diverging Nozzles with Constant-Radius Centerbody

Abstract

Several flow phenomena, such as recirculating wake flows or noise generation, occur in aerodynamic configurations with backward facing steps. In this context subsonic nozzles with constant-radius centerbodies exist, which enable fundamental research of these phenomena for M < 1. For the supersonic regime, however, the existing database and knowledge is limited. Therefore, the present work presents a design approach for a converging-diverging nozzle with constant-radius centerbody. For the nozzle throat, Sauer’s method is modified to include a centerbody. The method of characteristics is used for the subsequent supersonic portion. Comparing the analytical calculations to numerical simulations results in very good agreement and therefore underlines the feasibility of the chosen approach. Viscosity reduced the Mach number on the exit plane by 1.0 − 1.2% and therefore had little influence.