弯曲激波压缩曲面的二元高超声速进气道研究  

Study of Hypersonic 2D-Inlet with Leading Curved-Shock Wave Compression Ramp

作　　者：李大进[1] 高雄[1] 朱守梅[1] 

机构地区：[1]北京动力机械研究所高超声速冲压发动机技术重点实验室,北京100074

出　　处：《推进技术》2013年第11期1441-1447,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(90916029)

摘　　要：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Ma4～7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 2D hypersonic curved shock compression inlet has a shorter length and higher perform- ance. In order to investigate the ramp design method applying the curved shock compression between Ma = 4 and Ma = 7, the performance of the 2D hypersonic inlets with the curved shock compression and the isen- tropic compression have been investigated in comparison. 2D numerical simulation was conducted for the in- let according to the given law of constant wall pressure gradient so as to obtain flow characteristics. Numeri- cal results show that compression efficiency is high. Based on the comparison for the total pressure recovery ratio and the length of the inlets with the different initial angles, the ramp initial angle can not exceed 7~ and the length ratio of the inlet can be shortened about 10%. Compared with the curved shock inlet and the isentropic inlet, the total pressure recovery ratio of the curved shock inlet with law of constant wall pressure gradient drops about 3% -5% , but the design point of shock on lip can be dropped. In the end, three di- mensional waveride forebody with good waveride performance and 2D flow characteristics was conducted with the streamline trace, and shock wave surface was obtained near the design point.

关 键 词：高超声速 进气道 弯曲激波 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]