组合发动机可调进气道气动性能

Aerodynamic characteristics research on variable geometry inlet of combined cycle engine

为使涡轮/冲压组合发动机能在宽广的飞行高度、速度内飞行,设计一种组合发动机可调进气道气动结构.编制带黏性修正激波系结构预估程序,实现不同来流马赫数及来流攻角下,进气道内激波系结构布置及强度预估,并指导进气道可调楔板尺寸选取.考虑进气道附面层抽吸后,对来流在马赫数为1.6～4.0范围内,-2°,0°和+2°三种攻角下进气道二维流场进行数值计算,流场结构与二维带黏性修正激波系结构预估程序计算结果非常吻合,得到进气道在各工况条件下气动性能,分析了来流马赫数及攻角对调节规律及进气道性能特性的影响规律.

To enable the flight of turbo/ramjet combined cycle engine within exte nsive altitude and speed,the aerodynamic structure of a variable geometry inlet for combined cycle engine was designed in this paper.Estimation program of shock structure with viscous correction was compiled to estimate the shock structures and intensities in the inlet under different Mach numbers and attack angles.The choice of the variable panel length was governed by the program.Considering the boundary layer suction,two-dimensional flow fields of the inlet were simulated from Mach number 1.6 to 4.0 at attack angles of-2°,0°,＋2°.The structures of the flow fields were consistent with the computed results by the compiled progra m.Aerodynamic characteristics of the variable geometry inlet were acquired.The i nfluences of Mach numbers and attack angles on the adjustment rules and aerodyna mic characteristics of the inlet were analyzed.