根据矩形截面高超声速进气道前体的流动特征,对一种前体加宽型高超声速进气道试验方案开展了数值仿真及高焓风洞试验研究。首先,对不同前体宽度的高超声速进气道开展了三维数值仿真研究,结果显示:随着前体宽度的增加,进气道的流量系数和静压比逐渐增加,而总压恢复系数和隔离段出口马赫数逐渐减小,表现为先急后缓,且当来流马赫数和来流攻角变化时依旧保持上述变化规律。其次,对前体加宽型高超声速进气道试验方案开展了高焓风洞试验研究,结果表明:加宽前体可有效地提高进气道的流量系数,较为真实地反映此类进气道的流动特征,试验结果与数值仿真结果吻合较好。考虑到进气道性能参数随前体宽度变化规律表现为先急后缓,建议在试验条件下前体宽度比取0.5~0.8之间较为适宜。
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.
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