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针对现有定几何高超声速进气道低马赫工作时流量系数低、溢流阻力大,变几何高超声速进气道结构复杂、附加重量大、可靠性低等缺点,提出了一种基于激波形状控制的固定几何高超声速可调进气道概念,给出了其实现模式,并进行了初步的验证.研究结果表明,该可调进气道能够依靠自身的高压驱动来实现对口部波系、有效喉道面积的调节,使进气道在低马赫数下的流量系数相对于常规定几何高超声速进气道提高20%以上,前体阻力系数下降8%以上,其性能特征对于改善高超声速飞行器的低马赫数加速性能特别有利.
Aiming at the shortcomings of low Mach coefficient, large flow resistance, variable geometry hypersonic inlet structure, additional weight and low reliability, Shape control of fixed geometry hypersonic adjustable inlet concept, given its implementation mode, and carried out a preliminary verification.The results show that the adjustable intake port can rely on its own high-pressure drive to achieve the mouth of the wave system , The effective throat area adjustment, the inlet at low Mach number flow coefficient relative to the conventional fixed geometry hypersonic inlet increased by 20%, the precursor drag coefficient decreased by 8%, and its performance characteristics for improving the high The low Mach number acceleration performance of supersonic aircraft is particularly advantageous.