矩形转圆形高超声速内收缩进气道数值及试验研究

doi:CNKI:11-1929/V.20110217.1420.000

Abstract

Abstract: With pressure gradient on the wall of the inlet’s basic flow field increasing at the front part then decreasing at the rear part, using streamline tracing and varying section techologies, a hypersonic inward turning inlet with rectangular to circular shape transition integrated into 4° wedge forebody, is designed and investigated with numerical simulation and experimental method. The flow field structure and performance of the inlet are primarily obtained. The simulation results of design points and take-over speeds indicate that this inlet can operate normally over the Mach number range of 4-6 and has good performance with 4° angle of attack. The inlet model is tested in a hypersonic wind tunnel at Mach number 6 with 4° angle of attack. And the experimental results indicate that the scaled inlet model’s total pressure recovery is 0.45. It can generate a compression ratio of 41.2 and withstand a back pressure ratio of 200 relative to tunnel static pressure.

Key words: hypersonic inlets, basic flowfield, law of pressure rise, numerical analysis, wind tunnel test

CLC Number:

V231

NAN Xiangjun, ZHANG Kunyuan, JIN Zhiguang, SUN Bo. Numerical and Experimental Investigation of Hypersonic Inward Turning Inlets with Rectangular to Circular Shape Transition[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(6): 988-996.

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Numerical and Experimental Investigation of Hypersonic Inward Turning Inlets with Rectangular to Circular Shape Transition

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