典型几何和流动参数对高超声速进气道性能的影响

Effect of Geometry and Flow Parameters on Internal Compression Performance of Typical Two-Dimensional Hypersonic Inlets

用N-S方程模拟了一系列典型二元高超声速进气道内压缩通道及隔离段模型,模拟发现内压缩通道及隔离段增压比、温升比和总压恢复系数等性能参数主要受面积收缩比、内压缩通道收缩角、隔离段长高比等几何参数以及内压缩通道进口马赫数、密度、附面层厚度等流动参数的影响。内收缩比和内收缩通道收缩角的增大都会使压缩增强;隔离段内沿程平均温升比、马赫数和总压恢复系数曲线则均接近平行直线。内压缩通道进口马赫数的增大也会使压缩增强,但较小的进口马赫数可能引起分离,进而增大增压比;而进口密度增大使附面层变薄,对气流的压缩减弱;进口附面层厚度对沿程平均温升比、增压比以及马赫数的影响近似线性。

A series of internal contraction tunnels and isolators of hypersonic inlets are simulated by N-S equation. The performances （e. g. temperature rise ratio, pressure rise ratio, total pressure recovery） of internal contraction tunnels and isolators are affected by several geometry parameters （e. g. internal contraction ratio, convergence angle, isolator length/height ratio） and flow parameters （e. g. boundary layer thickness, Mach number and the density at the entrance to the internal contraction tunnel）. The increments of the contraction ratio and the convergence angle strengthen the internal compression. The lines of the average temperature rise ratio, the Mach number and the total pressure recovery along isola tors are a series of parallel lines. The increase of Mach number at the entrance also strengthen the compression, but the separation is potentially arised at too little Mach number, thus increasing pressure rise ratio. The density at the entrance weakens the boundary layer and the compression. The lines of boundary layer thickness to average temperature rise ratio, pressure rise ratio and Mach numbers along the flow are approximately linear.