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以弯曲激波压缩面设计的二元进气道具有较短的长度和较高的性能,研究了以等压力梯度弯曲激波压缩曲面设计的二元进气道一般性能,并以部分等熵压缩前楔板设计的二元进气道的一般性能与之作对比,以探讨前者在Ma 4~7高超声速范围进气道的外压缩面设计上的应用。对以等压力梯度设计的型面开展分析,进行了2D粘性计算并获得了稳定流场,显示进气道有较高的压缩效率。在相同总折转角条件下,通过对比不同起始角方案的进气道总压恢复和长度比,前楔板起始角不宜超过7°,进气道长度比可缩短约10%。在对比计算等压力梯度设计的进气道与部分等熵压缩进气道后,认为前者总压恢复性能要下降3%~5%,但激波封口设计点可以适当提前。最后尝试以流线追踪法扩展到三维乘波前体,在设计点附近获得平直的激波面,显示具较好的乘波特性和二元流动特征。
The binary inlet with curved compression surface has short length and high performance. The general performance of the binary inlet with bending compressive curved surface with equal pressure gradient is studied. The partial isentropic entropy Comparing the general performance of binary inlet before compression wedge design to explore the former in the Ma 4 ~ 7 hypersonic inlet outer compression surface design. The analysis of the profiles designed with equal pressure gradients performed a 2D viscous calculation and a steady flow field was obtained, showing a high compression efficiency of the inlet port. Under the condition of the same total turn angle, the starting angle of the front wedge should not exceed 7 ° and the length of the inlet length should be shortened by about 10% by comparing the total inlet pressure recovery and the length ratio of the different starting angles. Comparing the inlet and part of the isentropic compression inlet designed for isobaric gradient, the total pressure recovery performance of the former is expected to decrease by 3% ~ 5%, but the shock seal design point can be advanced properly. The last attempt to streamline tracing method to the three-dimensional wavefront precursors obtained in the vicinity of the design point of the flat shock wave surface, showing a better multiplier characteristics and binary flow characteristics.