高超声速混合模块冲压发动机亚燃模块进气道的高焓风洞试验研究

ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2007, Vol. 28 ›› Issue (4): 783-790.

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Wind Tunnel Tests of Hypersonic Inlets for Ramjet Modules of Ramjet scramjet Combined Engine

TAN Hui-jun,GUO Rong-wei

Internal Flow Research Center, Nanjing University of Aeronautics and Astronautics

Received:2006-03-29 Revised:2007-05-31 Online:2007-07-10 Published:2007-07-10
Contact: TAN Huijun

Abstract

Abstract:

The preliminary test study is conducted on hypersonic inlets for ramjet module of the ramjetscramjet combined engine at a Mach number of 6 in a high enthalpy tunnel. The performance and static pressure distributions of the inlet under different backpressure conditions are obtained. Results indicate:(1) The mass flow ratio of the inlet is greater than 0.98 at a Mach number of 6, at the throat section the total pressure recovery coefficient and the average Mach number are 0.52 and 2.68 respectively.

Key words: hypersonic , inlet, , ramjet, , ramjetscramjet , combined , engine, , wind , tunnel , test

CLC Number:

V211.3

TAN Hui-jun;GUO Rong-wei. Wind Tunnel Tests of Hypersonic Inlets for Ramjet Modules of Ramjet scramjet Combined Engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2007, 28(4): 783-790.

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Wind Tunnel Tests of Hypersonic Inlets for Ramjet Modules of Ramjet scramjet Combined Engine

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