马赫数可控的方转圆高超声速内收缩进气道试验研究

Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape with controlled Mach number distribution

基于反正切马赫数分布的弥散反射激波中心体轴对称基准流场,设计了方转圆内收缩进气道,并对其进行自由射流试验和数值仿真,获得该类进气道设计点的工作特性。试验结果表明:进气道顶板压力分布具有反正切曲线特征,总体性能优良且出口涡流区较小,上述设计方法可行有效。设计点时出口总压恢复系数达到0.561,增压比为26.2,临界反压约为135倍来流静压,对应的总压恢复系数为0.210。当带4°攻角时,进气道出口增压比增加49.6%的同时总压恢复系数降低了17.5%。

Based on the axisymmetric basic flowfield with diffusing reflected shock center body and arc tangent Mach number distribution,an inward turning inlet with rectangular-to-circular transition is designed.The experiment on the wind tunnel and numerical simulation are conducted to obtain the operation characteristics of the design point.The experimental results indicate that the pressure distribution of the top wall is characterized by an arc tangent curve.The inlet is of good overall performance,and the vortex region is small.In conclusion,the design method proposed is feasible and efficient.For the design point,the total pressure recovery coefficient is 0.561 and the compression ratio is 26.2at the exit section.The critical back pressure is about 135 times of the free stream static pressure,and the corresponding total pressure recovery coefficient is0.210.With 4°attack angle,the compression ratio increases by 49.6% but the total pressure recovery coefficient decreases by 17.5% at the exit section.