三维内收缩式进气道V形溢流口热流计算与分析

Investigation of Aerothermal Heating on V-Shaped Leading Edge of Inward Turning Inlet

为了获得流场特性和热流影响规律,将高超声速进气道中带有V形的溢流口进行简化,采用数值计算和实验相结合的方法研究了简化后V形溢流口的前缘热流,对比分析了不同前缘钝化构型、不同前缘角θ以及不同倒圆半径比R/r下V形溢流口的热流分布。结果表明,和钝头体以及旋成体相比,钝化的V形溢流口受到更加严重的热载荷,流场结构也更加复杂;改变前缘角θ并不能显著降低热流,可见通过改变前缘角θ对溢流口前缘热流改善能力有限;倒圆半径比R/r对V形溢流口热流影响明显,倒圆半径比R/r<6时,溢流口前缘气动受热剧烈,倒圆半径比R/r>6时,热流峰值降低且随倒圆半径比R/r变化不明显。在进气道设计中应综合考虑气动性能和热防护等因素进行合理取舍。

In order to obtain the flow field characteristics and the influence of aerothermal heating, the cowl of hypersonic inward turning inlet is simplified as V-shaped leading edge. By means of numerical simulations and wind tunnel tests,the simplified model is studied with different blunt configurations,angle（θ）of leading edge and ratio（R/r）of rounding radius and blunt radius. The results show that,comparing with blunt body and slender body,the V-shaped leading edge exists complex shock wave interference and suffers critical aerothermal heating. The heat flux reduces slightly and the peak value of it still keeps high level when angle is changed. In other words,it is limited to achieve thermal protection by changing angle of leading edge. The ratio of rounding radius and blunt radius impacts significantly the aerothermal heating of V-shaped leading edge. With increasing of ratio,the peak value of heat flux decreases significantly. Heat flux keeps greatly high level when R/r6 and Heat flux keeps steady low level when R/r6. Multi-factor,including aerodynamic performance and thermal protection,should be taken into account and be made a reasonable choice for designing in hypersonic inlet.