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提出了一种高超声速飞行器乘波前体的外锥形基准流场设计方法,在锥面马赫数分布规律给定的条件下,通过有旋特征线法实现反设计,提高了基准流场设计的灵活性。该基准流场通过锥形“下凹”弯曲激波和波后等熵压缩波系压缩气流,可以在较短的长度内完成高效压缩。基于反正切马赫数分布外锥形基准流场设计的乘波前体具有较高的容积率,乘波特性良好且出口均匀,设计点时有黏升阻比为1.89。另外,基于该乘波前体和马赫数分布可控的内收缩进气道给出了一种双乘波的前体与进气道一体化设计方案,实现了内外流分别独立乘波,充分发挥了乘波前体和内收缩进气道的各自优势。
A design method of outer conic reference flow field for hypersonic vehicle precursors is proposed. Under the condition of the Mach number distribution, anti-design is achieved by spin-line method, and the design of reference flow field is improved Flexibility. The reference flow field can be compressed efficiently in a shorter length by compressing the conical “concave ” flexural shock and post-wave isentropic compressional wave system. The wavefront precursors designed based on the out-tapered Mach-Zehnder reference flow field have high volumetric ratio, good multiplying wave characteristics and uniform exit. The drag-and-drag ratio at design point is 1.89. In addition, a dual-wave front-to-port integrated design scheme based on the controllable multiplier precursors and Mach number distribution of internal contraction inlet is provided, Exert the respective advantages of multiplying the wavefront precursors and deflating the intake port.