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基于密切曲内锥乘波前体进气道的一体化设计方法,生成了内外流匹配的一体化三维乘波前体进气道理论构型。在几何约束条件下,完成了实用化构型设计,其总收缩比4.6,内收缩比2.0。开展了来流马赫数3.0,3.5,4.0条件下的风洞试验研究。试验研究结果表明,一体化前体进气道可以在来流马赫数3.5及以上自起动;在马赫3.5和4.0,攻角0°时,其流量捕获系数分别为0.65和0.73,最大抗反压性能分别为26倍和38倍的来流压力。本文的试验研究结果,证实了设计的一体化密切内锥乘波前体进气道能够在吸气式高超声速飞行器的低马赫数端正常工作,并具备较高的流量捕获系数。
Based on the integrated design method of the inlet of in-plane Quasi-coning-wave precursors, a theoretical configuration of the inlet of the integrated 3D-wave-like precursors is derived. Under geometric constraints, the practical configuration design has been completed with a total shrinkage ratio of 4.6 and an internal shrinkage ratio of 2.0. Wind tunnel experiments were carried out at Mach 3.0, 3.5 and 4.0. Experimental results show that the integrated precursor inlet can self-start at a Mach number of 3.5 and above. At Mach 3.5 and 4.0 and an attack angle of 0 °, the flow trapping coefficients are 0.65 and 0.73 respectively. The maximum anti-back pressure The performance is 26 times and 38 times the flow pressure. The experimental results of this paper confirm that the designed integrated in-cone cone-wave precursor inlet port can work normally at the low Mach number end of the aspirated hypersonic vehicle and has a high flow rate capture coefficient.