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针对一种冲压发动机用双下侧布局二元混压式进气道,利用经过试验验证的数值方法分析其流场特征和气动性能。研究结果表明:1)在高于起动马赫数2.25下一定反压范围内,由于气动喉道的出现使结尾激波系可以停留在收缩通道内;2)随着来流马赫数的增大,进气道的总压恢复系数下降;而流量系数先上升,当激波贴口后基本保持不变;3)在一定迎角范围内,进气道的总压恢复系数和流量系数提高,但当迎角增大至进气道不起动时,随着迎角的增大,进气道的总压恢复系数和流量系数基本不变;4)随着侧滑角的增大,两侧进气道总压恢复系数均是下降的。
For a kind of ramjet engine with double lower side layout of the binary mixed-pressure inlet, the use of the experimental verification of numerical methods to analyze the flow field characteristics and aerodynamic performance. The results show that: 1) At the pressure range of 2.25, which is higher than the starting Mach number, the end shock system can stay within the shrinkage channel due to the occurrence of pneumatic throat; 2) With Mach Mach number increasing, The total pressure recovery coefficient of the inlet decreases, while the flow coefficient first increases and remains basically unchanged after the shock wave is applied. 3) The total pressure recovery coefficient and the flow coefficient of the inlet increase within a certain angle of attack, When the angle of attack increases until the inlet does not start up, the total pressure recovery coefficient and flow coefficient of the inlet will be basically unchanged with the increase of the angle of attack. 4) With the increase of the side slip angle, The total airway pressure recovery coefficient decreased.