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为了研究超声速铲形进气道的气动特性,针对固定几何超声速铲形进气道,利用数值仿真计算及风洞试验,获得了来流马赫数Ma∞=2.5,3.0,3.5,4.0,攻角α=-6°,-3°,0°,3°,6°,8°以及侧滑角β=3°,6°的临界性能。研究结果表明该超声速进气道具有良好的攻角特性,随着攻角的增加,总压恢复系数和流量系数增加;6°侧滑角以内进气道总压恢复系数和流量系数变化量很小。该进气道与飞行器前体一体化设计,能够很好地适应大空域、宽马赫数范围工作需求。
In order to study the aerodynamic characteristics of supersonic shovel inlet, aiming at fixed geometry supersonic shovel inlet, numerical simulation calculation and wind tunnel test were used to obtain Mach Mach number = 2.5, 3.0, 3.5, 4.0, angle of attack α = -6 °, -3 °, 0 °, 3 °, 6 °, 8 ° and the side slip angle β = 3 °, 6 ° of the critical performance. The results show that the supersonic inlet has a good angle of attack characteristics, with the angle of attack increases, the total pressure recovery coefficient and flow coefficient increases; 6 ° side slip angle within the inlet total pressure recovery coefficient and flow coefficient is very variable small. The integrated design of the air intake and the precursor of the aircraft can well adapt to the needs of large-area and wide-range Mach number work.