修型对高超声速前体／进气道性能的影响分析

摘要

The benchmark configuration of typical two-dimensional hypersonic forebody and inlet was modified at the shoulder point region by a curved surface.Curved surface models with different radius and different length were simulated by CFD method.Effects of arc transition scheme on forebody and inlet per-formances were investigated.Computation results indicate that the compress efficiency of forebody and in-let at design point increases ,but the mass flow rate decreases a little.The difference of performance be-tween curved surface modified and original model at off-design Mach number are similar with design con-dition,while the total pressure recovery is obviously higher than the original model in small and negative angle of attack conditions.The results show that curved surface can partially improve the performance of forebody and inlet at design and off-design conditions.The research results can provide a reference for in-tegrated design of scramjet and trajectory optimization of hypersonic cruise vehicle.%采用圆弧形曲面对常规二元高超声速前体／进气道上壁面肩点处进行局部修型.对修型后的前体／进气道进行了数值分析,研究了不同半径和不同长度的弧形过渡曲面对前体／进气道性能的影响.计算结果表明:采用弧形过渡可以提高设计点下前体／进气道的压缩效率,但流量系数却略有下降.在非设计马赫数状态下,修型前后前体／进气道的性能差异与设计点基本相当;在小的正迎角以及负迎角状态下,修型后前体／进气道的总压恢复系数高于原模型,总体性能明显优于原模型.分析表明弧形曲面过渡可以部分提高前体／进气道的设计点和非设计点性能.研究结果对超燃冲压发动机的总体设计和高超声速飞行器的轨迹优化具有一定参考价值.