Abstract: The numerical simulation of infrared radiation from cavitation,plume and cavitation plume composition of aeroengine high speed exhaust system has been conducted.This is achieved through solving the radiation transfer equation (RTE) of dissipation emission medium by means of closure domain theory and Goody band model on the basis of 3 D flowfield calculation of aeroengine exhaust system.The results of computation have been compared with that of practical engine ground test.The investigation results indicated that the relative tolerance of infrared radition is less than 30% and the infrared radition distribution of computation is roughly consistent with that of engine test.The computation methods and code referred could be applied to estimating the infrared radition of practical aeroengine exhaust system.