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为了适应TBCC发动机宽马赫数进气需求,基于Oswatitsch的最佳波系理论和CFD技术,考虑变比热、激波与附面层干扰等因素的影响,分别选取飞行马赫数Ma=4,高度H=21300m和飞行马赫数Ma=6,高度H=26600m为设计点,对TBCC发动机二级混压式进气道进行了初步设计,分析并比较了两种方案进气道的设计点和非设计点性能及二维流场。计算结果表明:不考虑粘性影响,本文设计的进气道能够满足沿飞行轨迹的TBCC发动机性能要求,具有良好的内外流特性。
Based on Oswatitsch’s theory of optimal wave system and CFD technology, in consideration of the influence of variable heat of ratio, shock wave and interference of surface layer on the TBCC engine, the Mach number of flight is chosen as Ma = 4, height H = 21300m and Mach number of flight Ma = 6, height of H = 26600m as the design point, the preliminary design of TBCC engine’s two-stage mixed intake was carried out, the design points and non-design of two schemes were analyzed and compared Design point performance and two-dimensional flow field. The calculation results show that, regardless of the viscous effect, the inlet designed in this paper can meet the performance requirements of the TBCC engine along the flight path and has good internal and external flow characteristics.