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提出了一种进气道内收缩比可控、包括唇口后退等几何动作的变几何进气道的设计思路,给出了具体的设计过程及影响因素.据此开展了二元高超声速定、变几何进气道气动方案设计,并进行了细致的数值模拟,给出了进气道气动性能参数随来流马赫数的变化规律,将定、变几何进气道气动性能进行了对比分析,结果显示:设计马赫数下,定、变几何进气道气动性能基本相同;非设计马赫数下,变几何进气道的流量系数明显高于定几何方案,且马赫数越低,两者相差越大.静压比、温升比、总压恢复系数及隔离段出口马赫数则相差不大.
A design idea of a variable geometry intake port with controllable contraction ratio in the intake port and geometry movement including lip recession is given and the specific design process and influencing factors are given.According to this, The aerodynamic design of variable geometry inlet is carried out. The numerical simulation of the aerodynamic performance of the inlet is carried out. The changing law of the aerodynamic performance parameters of the inlet with the flow Mach number is given. The results show that under the design Mach number, the aerodynamic performance of fixed and variable geometry inlet is basically the same. Under non-design Mach number, the flow coefficient of variable geometry inlet is obviously higher than that of the fixed geometry, and the lower the Mach number, the difference between the two The bigger the static pressure ratio, the temperature rise ratio, the total pressure recovery coefficient and the isolated section exit Mach number have little difference.