槽对超声速混压式进气道性能及边界层的影响  

Performance and boundary layer of flow in axisymmetric mixed-compression supersonic inlet with cavity

作　　者：莫展[1] 王新月[1] 未军光[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2009年第2期302-306,共5页Journal of Aerospace Power

摘　　要：为提高定几何超声速混压式轴对称进气道的性能,应用在进气道不同位置开槽的方法,研究了在各级锥体上、锥体折角处开槽时锥体上的边界层变化,研究了多工况下开槽对进气道的总压恢复系数、流量系数、增压比和起动性能产生的影响.结果表明:开槽一方面改变了超声速进气道锥体上的波系分布和进口马赫数,另一方面也使槽后边界层厚度增加,改变了边界层内的速度分布,使摩擦阻力增大.二级锥面上槽后边界层厚度模型1比原型大33.3%,模型2比原型大16.7%,三级锥面上槽后边界层厚度模型1比原型增加52.4%,模型2比原型增加9.1%.开槽使高马赫数下的总压恢复系数有所增加,其增加量随来流马赫数的变化而变化.在马赫数为4.0的设计状态下,折角处开槽可使进气道的总压恢复系数提高1.8%,锥体上开槽可以提高4.3%.锥体折角处开槽对流量系数和起动性能影响不大.In order to improve the performance of axisymmetric mixed-compression supersonic inlet with fix-geometry, the performance of a supersonic inlet with cavities at the cone surface or the cone＇s corners was investigated by the numerical simulation. The effects of the cavities position on the cone on the performance of the inlet and the boundary-layer were presented. On the one hand, the shocks on the cones and the inlet＇s entrance Mach number were changed. On the other hand, the thickness of the boundary layer behind the cavities was increased and the velocity distribution in the boundary layer was also changed. When the cavities were at the cone＇s surface, the boundary layer thickness behind the cavities at the second and the third cone surface increased 33. 3% and 52. 4%, respectively. When the cavities were at the cone＇s corners, the boundary layer thickness behind the cavities increased 16.7% and 9.1%, respectively. The inlet＇s pressure recovery and the pressing ratio with cavities were higher than no cavities at high Mach number （3.7 to 4.5）. Under design condition, the inlet＇s pressure recovery at the cavities of the cone＇s corners increased about 1.8 %, and the pressure recovery at the cavities at the cone surface increased about 4.3 than no cavity. Besides, the mass capture ratio and starting Mach number were not influenced by the cavity at the cone＇s corners.

关 键 词：超声速轴对称进气道 数值模拟 凹槽 边界层 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]