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为了研究攻角导致的来流条件非定常变化对高超声速进气道性能的影响,以一个设计马赫数为6的侧压式进气道为研究对象,结合数值模拟的方法,在马赫数为3.85条件下进行了攻角动态变化的风洞实验,攻角变化范围为0°~8.2°,最大频率达到10.4 Hz.研究结果表明:工作在大攻角时,侧压式进气道出现不起动现象,流场特征出现很大变化;攻角动态变化时,进气道重复出现起动-不起动-再起动现象,由于受到壁面运动的影响,壁面点压力随攻角的变化曲线出现一定的迟滞现象,这在不起动时尤为明显;当进气道攻角动态频率增加时,进气道不起动时的攻角逐渐增加,而再起动时的攻角逐渐减小.
In order to study the influence of unsteady inflow conditions on the performance of hypersonic inlet due to angle of attack, a side-pressure inlet with design Mach number of 6 was selected as the research object. Combined with numerical simulation, 3.85 wind tunnel experiment with dynamic change of angle of attack was carried out, the angle of attack ranged from 0 ° to 8.2 ° and the maximum frequency reached 10.4 Hz.The results show that the side pressure inlet does not appear when working at high angle of attack When the angle of attack changes dynamically, the inlet recovers from start to stop and restarts. Due to the influence of the wall motion, the point pressure on the wall appears a certain change with the angle of attack Hysteresis phenomenon, which is especially obvious when not starting. When the dynamic frequency of air inlet attack angle increases, the attack angle of air intake does not start increasing while the attack angle of restarting decreases gradually.