A Method for Predicting Inlet Temperature Distortion Caused by Missile Plumes

Abstract

In this paper we provide information for the design of a 3D external compression inlet system which is affected by the exhaust plume of a missile. The inlet 3D flow field has been simulated by 3D time dependent Euler equations and solved using the J. D. Denton scheme. The total temperature and total pressure distributions are obtained for a quasi–steady state and the temperature increment (DT) and its variation rate (RDT) are calculated. Two definitions of DT and RDT are given and a simple condition has been put forward for calculating the inlet flow field with serious upstream distortion. Finally, an attenuation law is presented which estimates the temperature distortion in the inlet duct from the inlet entrance to the exit for different conditions and different intervals.