EXPERIMENTAL AND NUMERICAL INVESTIGATION OF HYPERSONIC JAWS INLET

被引：1
|
作者：
Dong, Hao [1 ]
Wang, Cheng-Peng [1 ]
Cheng, Ke-Ming [1 ]
机构：
[1] Nanjing Univ Aeronaut & Astronaut, Coll Aerosp Engn, Nanjing 210016, Peoples R China
来源：
MODERN PHYSICS LETTERS B | 2010年 / 24卷 / 13期
关键词：
Hypersonic inlet; inward turning; streamline traced; boundary layer correction; wind tunnel test;
D O I：
10.1142/S0217984910023748
中图分类号：
O59 [应用物理学];
学科分类号：
摘要：
In order to obtain the flow field characteristics and the influence of boundary layer, numerical simulations and wind tunnel tests are conducted for two streamline traced Jaws inlets at Mach number 7. The inlets are designed based on a flow field with 8-7 planar shock wave (the ramp in pitch plane is inclined at 8 degrees to the free stream and in yaw plane is inclined at 7 degrees to the free stream, yielding planar shocks). In the study, the static pressure distributions were measured and analyzed along the plane-symmetric centerline of the inlet with and without the boundary layer correction, respectively. Results show that boundary layer correction can obviously weaken the viscous influence to the inlet, increasing the mass flow coefficient and improving total pressure recovery.
引用
收藏
页码：1409 / 1412
页数：4
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