高超声速弯曲激波压缩侧压式进气道数值研究

采用壁面马赫数呈线性分布的曲面压缩系统改进参考侧压式进气道的顶板,得到弯曲激波压缩侧压式进气道,并与参考侧压式进气道进行了比较.数值研究结果表明:设计状态无黏时曲面压缩顶板壁面马赫数分布与给定的马赫数分布基本一致,并且有黏时其壁面压力分布也与二维曲面的基本相同;同参考侧压式进气道相比,顶板采用曲面压缩能够一定程度地改善壁面压力分布,使其末端压力梯度变化平缓;并且非设计状态下的性能也得到有效地改善,特别是来流马赫数为4时,其流量系数提高6.0%、达到0.799,喉道截面总压恢复系数提高1.9%;来流马赫数为5时,其流量系数提高5.2%、达到0.909,喉道截面总压恢复系数提高3.2%.随着攻角增大,该进气道流量捕获能力增强、隔离段出口截面流场畸变减小,但喉道截面总压恢复系数下降剧烈.

Numerical investigation of hypersonic curved shock sidewall compression inlet

Curved surface compression system with wall Mach number linear distribution was used to improve the topwall of the reference sidewall compression inlet, then curved shock sidewall compression inlet was obtained and Compared with the reference sidewall compression inlet. The numerical result shows that: the wall Mach number distribution of topwall with curved surface is consistent with the given Mach number distribution at the design and inviscid condition, and its wall pressure distribution is basically the same as that of two-dimensional curved surface at viscous condition. Compared with the reference sidewall compression inlet, when the topwall used curved surface compression, its wall pressure distribution was improved to a certain extent, and the pressure gradient at the end of surface changed smoothly. And the performance of off-design condition is improved effectively; especially the mass flow capture ratio increases 6% and reached 0.799 at inflow Mach number of 4, and the total pressure recovery of throat section increases 1.9%. At inflow Mach number of 5, its mass flow capture ratio increases 5.2% and reached 0.909, and the total pressure recovery of throat section increases 3.2%. With the increase of the angle of attack, the inlet's ability of capturing mass flow improved and the flow field distortion of isolator exit section decreased. But the total pressure recovery of throat section decreased sharply.