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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。
According to the flow characteristics of the inlet of a rectangular section hypersonic inlet, a numerical simulation and a high-enthalpy wind tunnel experiment were carried out on a precursor widened-type hypersonic inlet experiment. Firstly, three-dimensional numerical simulation of hypersonic air inlets with different precursors width is carried out. The results show that the flow coefficient and static pressure ratio of air inlet increase gradually as the precursor width increases, and the total pressure recovery coefficient The Mach number at the exit of the isolation section gradually decreases, which is characterized by the first emergent slowness and the change at the same time when the incoming Mach number and the attack angle of the incoming stream change. Secondly, a high enthalpy wind tunnel experiment was carried out on the precursor widened hypersonic air inlet test. The results show that widening the precursor can effectively improve the flow coefficient of the inlet, which can more accurately reflect the intake air Road flow characteristics, the experimental results and numerical simulation results are in good agreement. Taking into account the performance parameters of the inlet with the precursor of the law of change for the first to postpone the slow, it is proposed under the test conditions precursor width ratio of 0.5 to 0.8 is more appropriate.