马赫数可控的方转圆高超声速内收缩进气道试验研究
收稿日期: 2015-10-13
修回日期: 2015-12-28
网络出版日期: 2016-02-22
基金资助
国家自然科学基金（90916029，91116001 ）
Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape with controlled Mach number distribution
Received date: 2015-10-13
Revised date: 2015-12-28
Online published: 2016-02-22
Supported by
National Natural Science Foundation of China (90916029, 91116001)
李永洲 , 张堃元 , 孙迪 . 马赫数可控的方转圆高超声速内收缩进气道试验研究[J]. 航空学报, 2016 , 37(10) : 2970 -2979 . DOI: 10.7527/S1000-6893.2016.0035
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 26.2 at the exit section. The critical back pressure is about 135 times of the free stream static pressure, and the corresponding total pressure recovery coefficient is 0.210. 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.
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