中文摘要：

利用计算流体动力学（CFD）技术分析了进气道质量流量差异对外表面压力系数分布的影响,并通过对发动机进气道唇口的反设计优化,使涡轮动力模拟器（TPS）试验时的外表面压力分布与真实质量流量下的压力分布基本一致.通过对发动机唇口修正,可提高2.4m跨声速风洞高速带动力模拟风洞试验的准度.

英文摘要：

Computational fluid dynamics（CFD） was adopted to investigate the effects of mass flow rate difference on nacelle outer surface pressure coefficient distribution.Inverse design optimization technique was used in engine nacelle lip correction in order to adjust the turbofan propulsion simulators（TPS） outer surface pressure distribution to make it identical with that of the real engine.The engine nacelle lip inverse design method can be used in 2.4 m transonic wind tunnel to improve jet engine flow simulation test accuracy.