空天飞机进气道的气动设计

应用一维气体流动的关系式推导出高超声速吸气式发动机的比冲公式,给出了计算进气道效率和面积比的公式。重点介绍了 NASA Langley 研究中心用于一体化超燃冲压发动机概念的固定几何形状、侧壁压缩的进气道的气动设计,包括主要几何参数如收缩比、宽高比、侧壁的后掠角与压缩角等的选择和燃料喷注支柱的设计。讨论了这种类型进气道的起动问题。最后,介绍了这种类型进气道的风洞试验技术与计算流体力学的方法。根据试验结果和计算结果,分析了这种类型进气道的性能。

THE AERODYNAMIC DESIGN OF INLET FOR AEROSPACE PLANE

The formula of specific impulse for air breathing enginesis deduced using the relationships of one-dimensional gas flow.Theformulas of efficiency and ratio of area for inlet are given.It putsemphasis on the aerodynamic design of the fixed gedmetry and sidewallcompression inlet for an integrated scramjet concept in NASA LangleyResearch Center.It includes the choice of the primary geometric param-eters,such as contraction,width-height ratio,sweep angle and com-pression angle of sidewall and design of the fuel injection struts.Theproblem of starting for this type of inlet is discussed.The technologyof the wind tunnel testing and methods of the computational fluid dy-namics for this type of inlet are introduced.Based on the results of thecomputation and the testing,the performance of this type of inlet isanalysed.