高超声速飞行器二元进气道试验和计算  

Through-flow experiment and calculation of two-dimensional inlet for hypersonic cruise vehicles

作　　者：焦子涵[1] 邓帆[1,2] 袁武[3] 王雪英[4] 陈林[1] 董昊[5] 

机构地区：[1]中国运载火箭技术研究院空间物理重点实验室,北京100076 [2]谢菲尔德大学机械工程学院 [3]中国科学院计算机网络信息中心超级计算中心,北京100190 [4]北京临近空间飞行器系统工程研究所,北京100076 [5]南京航空航天大学航空宇航学院,南京210016

出　　处：《固体火箭技术》2016年第4期470-475,487,共7页Journal of Solid Rocket Technology

摘　　要：设计了一种吸气式面对称高超声速飞行器,针对进气道性能,分别在两座风洞开展通流试验研究。针对第1次风洞试验大攻角状态（α=8°）测量值偏离线性的问题,辅助采用数值模拟手段分析原因,并对试验方案进行改进设计,解决了首次试验出现的问题。结果显示,在典型状态（Ma=5～6）下,进气道起动正常,性能良好,具有一定的抗侧滑能力;随来流马赫数增加,进气道流量系数增大,总压恢复系数减小,计算结果和试验结果一致;试验结果和数值计算的差异主要表现为基本测压方案α〉4°后,流量系数和总压恢复系数出现严重的非线性。数值模拟结果表明,主要原因为模型支撑方式及测压方式所引起的偏差,通过改进试验方案,解决了大攻角状态下测量值偏离正常趋势的问题。The performances of a two-dimensional inlet with hypersonic cruise vehicles configuration were investigated by wind tunnel experiments and CFD simulations in this article. A hypersonic cruise vehicle integrated aerodynamics and propulsion was designed. CFD simulations and two wind tunnel tests were carried out in two different wind tunnels to examine the hypersonic performances of the inlet. Though analyzing the results of the first wind tunnel experiment,an improved test scheme was carried out. The pressure measuring experiments results show that： The inlet was able to start under free stream mach number from 5.0 to 6.0 at interval of 1.0,even considering the yaw angle of 4°. The total pressure recovery coefficient and mass flow ratio of the inlet satisfied the requirements of design through analyzing the monitoring results. The total pressure recovery coefficient of the inlet decreased as the mach number of flow increased,mass flow ratio increased linearly as the angle of attack increased; the total pressure recovery coefficient and the mass flow ratio of experiment agreed well with the CFD results,even the angle of attack is more than 4°. There were differences of the changing trend of total pressure recovery coefficient and mass flow ratio between the two experiment results when the angle of attack is more than 4° because of the differences of the two test scheme,the problem of departure from the regular changing trend was solved after improving the test scheme.

关 键 词：二元进气道 巡航飞行器 通流试验 超燃冲压发动机 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]