一种前体加宽型高超声速进气道试验方案研究

doi:CNKI:11-1929/V.20120113.1023.008

Abstract

Abstract: The flow in a hypersonic forebody/inlet with a rectangular section is analyzed with three-dimensional numerical simulation in this paper, and the flow characteristics with different forebody widths are also discussed. The result shows that with the increase of the forebody width, the mass flow ratio and static pressure ratio also increase, while the total pressure recovery coefficient and Mach number of the isolator exit decrease. This variation is consistent at different freestream Mach numbers and angles of attack. A preliminary test verification is conducted on different forebody width hypersonic inlets at Mach number of 5.0 and 6.0 in a high enthalpy tunnel. The static pressure distributions in the flow of the hypersonic inlets are obtained. The result indicates that the numerical simulation results represent the basic flow characteristics and show a consistent trend with the experimental results. The numerical simulation results are credible. Both the numerical simulation and the experimental result show that the dilated forebody experiment method of the hypersonic inlets with rectangular sections is feasible, and the forebody width ratio within the range 0.5-0.8 is appropriate.

Key words: aerospace propulsion system, hypersonic inlet, forebody width, rectangular section, experimental project

CLC Number:

V211.3

YUAN Huacheng, GUO Rongwei. Investigation of an Experiment Project of Hypersonic Inlet with Different Forebody Widths[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, (4): 617-624.

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Investigation of an Experiment Project of Hypersonic Inlet with Different Forebody Widths

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