展向截断曲面乘波压缩进气道气动布局

描述了所设计的展向截断曲面乘波压缩进气道.其特点是采用曲面乘波压缩前体,前体进气道压缩面基准流场由等熵压缩波轴对称流场组成,三维乘波面采用密切曲锥方法由前缘线各点流线跟踪拟合构成流面.乘波面根据飞行器和发动机的宽度要求进行了截断.数值计算和风洞试验结果表明:与相同几何收缩比的四波系压缩进气道相比,在马赫数为4.5时,曲面乘波压缩进气道流量系数提高12%,总压恢复系数提高39%;在马赫数为6时,曲面乘波压缩进气道流量系数提高4%,总压恢复系数提高50%.超然冲压发动机性能明显提高. 

Aerodynamic layout of spanwise truncated curved waverider compression inlet

A new osculating curved cone (OCC)method for streamlining tracing axisymmetric flow fields of isentropic compressing waves was used to design the waverider lower surface and inlet lip inner surface.The waverider surface was spanwisely truncated according to the constraint of the vehicle's and engine's width.The numerical and experimental analyses show that OCC waverider inlet has some advantages compared with the same compression ratio four-stage ramp inlet. At Mach number is 4.5,the new inlet's capture mass flow rate increases by 12% and total pressure recovery coefficient increases by 39%.At Mach number is 6,the new inlet's capture mass flow rate increases by 4% and total pressure recovery coefficient increase by 50%.The supersonic combustion ramjet engine's performance is efficiently increased too.