超声速轴对称进气道流场的数值模拟

利用有限体积法求解二维轴对称可压缩N-S方程，对超声速弹用进气道内外复杂流场进行了数值模拟，数值格式为二阶迎风格式，所得流场结构清晰。研究结果表明：随着来流马赫数的增加，总压恢复系数随之下降，稳定工作范围增大，同时流量系数逐渐增大，在激波贴口后流量系数基本保持不变；在同一来流马赫数的超临界状态下，随着进气道出口反压的提高，结尾正激波向喉道方向移动，结尾激波损失减小，总压恢复系数提高，进气道出口马赫数减小，出口流场畸变程度降低。

Numerical Simulation of Supersonic Axisymmetric Inlet Flow Field

The complex flow fields of a supersonic ramjet inlet were numerically simulated by 2D axisymmetric compressible N-S equation solved with infinite volume method and second order upwind scheme,to obtain clear flow structure.The results show that,with the increase of inflow Mach number,the total pressure recovery coefficient reduces,stable operating range increases,flow coefficient increases gradually and keeps being nonvariant when the cone shock attaches the cowl lip;at the supercritical operation condition ...