关键词: 超燃冲压发动机+;喷管;性能预测;数值仿真

Abstract: Relations of the internal thrust and specific impulse with the nozzle exit pressure have been established by means of one-dimensional fluid dynamics conservation models and chemical equilibrium hypothesis.With these new relations,difficulties in estimating the performance of scramjet engines based on experimental measurements can be removed.Thrust augmentations of experimental scramjet combustors have been obtained from the present relations and compared with the measurements on thrust increment to calibrate the combustion efficiencies.The thrust performance of the scramjet engine is estimated,and the curves of internal thrust coefficient,specific impulse and nozzle exit pressure are obtained based on the nozzle exit cross section,which can provide engineering basis for the integral performance assessment and optimal design of the scramjet engine and is valuable for experimental study.

Key words: Scramjet engine+;Nozzle;Performance prediction;Numerical simulation