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对一种设计马赫数为5的一级二元混压式进气道再入大气层过程典型状态进行了仿真和风洞试验,得到了该进气道典型状态下的气动特性.结果表明:当来流马赫数高于设计马赫数(为5)时,进气道外压斜激波系提前汇合,与唇罩入射斜激波相互作用,产生了波-波干扰;尽管发生了流动分离,但当来流马赫数为7和6时进气道出口上游气流紊流度分别不超过3.337和3.256,且流道内动态压力信号的功率谱密度呈现白噪声特征,不会对发动机造成结构损伤.因此,对于宽来流马赫数工作范围的进气道来讲,为了提供足够的流量,可以适当降低进气道的设计马赫数.
A typical state of reentrant atmospheric inlet with a Mach number of 5 was simulated and the wind tunnel test was carried out and the aerodynamic characteristics of the typical inlet of the inlet were obtained.The results show that when When the Mach number is higher than the design Mach number (= 5), the inlet shock wave is prematurely converged and interacts with the lip shock incident shock wave, resulting in wave-wave interference. Although the flow separation occurs, The turbulence of the upstream airflow at the outlet of the inlet is no more than 3.337 and 3.256 respectively when the flow Mach number is 7 and 6, and the power spectral density of the dynamic pressure signal in the flow channel is characterized by white noise without causing structural damage to the engine. , For wide inlet Mach range of inlet, speaking, in order to provide adequate flow, you can properly reduce the inlet design Mach number.