Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet
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Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet
Vol. 22, Issue 3, (2007)
作者机构:
南京航空航天大学能源与动力学院,江苏,南京,210016
作者简介:
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DOI:
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Published:2007
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SUN Bo, ZHANG Kun-yuan, JIN Zhi-guang. Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet[J]. 2007, 22(3).
DOI:
SUN Bo, ZHANG Kun-yuan, JIN Zhi-guang. Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet[J]. 2007, 22(3).DOI:
Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet
A wind-tunnel testing of a streamline traced hypersonic Busemann inlet
with a designed Mach 5.3 and shrinkage ratio CR=5
was conducted at Mach 3.85 to study its starting and overall performance as well as back-pressure capability below Mach 5.3 conditions.The results show that
the inlet can be started automatically at Mach 3.85;the flow coefficient of inlet is 0.83
the overall pressure recovery coefficient is 0.78
with a Mach number 2.01 and a compression ratio of 11.92;the inlet can withstand a maximum back-pressure of 34 times static pressure.