非传统激波封口设计在高超声速进气道中应用可行性研究

Feasibility of Applying a Non-Traditional Shock-on-Lip Design to Hypersonic Inlet

在马赫数4,5,6条件下借助轴对称数值模拟对4个高超声速轴对称进气道性能,即传统激波封口进气道、非传统激波封口进气道、改进非传统激波封口进气道和弯曲激波进气道,进行了比较研究。传统激波封口设计要求进气道各道外压缩激波在设计状态一起交于唇口,非传统激波封口设计要求各道外压缩激波分别在不同马赫数下交于唇口。结果表明:与传统激波封口进气道相比,非传统激波封口进气道在非设计状态的流量系数明显更高但在设计状态的总压恢复系数偏低;合理地改进设计能够减少非传统激波封口设计造成的总压损失。

Performance of four hypersonic triple-cone inlets,namely,a traditional shock-on-lip inlet,a nontraditional shock-on-lip inlet,an improved non-traditional shock-on-lip inlet and a curved shock inlet,was investigated by axisymmetric numerical simulation at Mach number 4,5,6,respectively. The non- traditional shock-on-lip design requires the shock waves of an inlet to meet the cowl lip respectively at different Mach numbers,which is different from the traditional shock-on-lip design that requires external compression shock waves to meet the cowl lip together at the design condition. Results show,compared with the traditional shock-on-lip inlet,the non-traditional shock-on-lip inlet delivers obviously higher flow rate coefficient at off-design conditions but lower total pressure recovery coefficient at design condition. Proper improvement design can reduce the total pressure loss caused by the non-traditional shock-on-lip inlet design.