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针对进气道内型面存在较大弯段而导致的流动分离问题,提出了一种对进气道出口弯段进行导流控制的概念,设计了3种不同的导流格栅方案,采用数值仿真方法对不同导流格栅方案的超声速进气道流动进行了对比分析,获得了不同导流格栅对进气道流场结构和工作性能的影响特性.结果表明:利用格栅对进气道进行导流控制,可以改善进气道出口弯段的流场结构和压力分布,避免进气道出口发生流动分离.通过对格栅型面进行优化可以显著改善进气道的工作性能,采用类翼型导流格栅的进气道性能改善幅度最大,马赫数为3.5条件下,其稳定工作裕度和出口总压恢复系数分别提高10.3%和9.8%,冷流内阻降低5.3%.
In order to solve the problem of flow separation caused by the large curved section of the inlet profile, a concept of diversion control of the curved section at the outlet of the intake duct is proposed. Three different schemes of diversion grid are designed, Simulation results show that the effect of different diversion grids on the structure and working performance of the inlet flow field is contrasted and analyzed with the supersonic inlet flow of different diversion grid schemes.The results show that: The flow diversion control can improve the flow field structure and pressure distribution at the outlet of the inlet and avoid the flow separation at the inlet of the inlet.Through optimizing the grille surface, the working performance of the inlet can be significantly improved, Airfoil diversion grille inlet performance improvement at maximum Mach 3.5, the stable working margin and the total outlet pressure recovery coefficient increased by 10.3% and 9.8%, respectively, cold flow resistance decreased by 5.3%.