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针对超燃进气道湍流边界层/激波干扰引起的分离问题,采用基于5阶WENO数值格式的大涡模拟(LES)方法开展流场湍流非定常预测,旨在分析进气道湍流化技术实现进气道起动的可行性。研究表明,平板激波/湍流边界层干扰(STBLI)问题,LES方法能够清晰、可靠预测反射、分离激波形成过程及激波与充分发展湍流边界层的相互干扰,定量结果与试验一致;进气道研究方面,层流状态下,激波干扰产生强分离,导致进气道堵塞,而采用湍流化控制后试验和计算均表明流场分离明显减小,流场稳定且无明显堵塞现象,进气道可以起动,总压恢复系数达到要求,该结果表明,利用强湍流化减弱分离,实现进气道起动思想是可行的。
In order to solve the problem of separation caused by the turbulent boundary layer / shock disturbance of the scramjet, a large eddy simulation (LES) method based on the fifth-order WENO numerical scheme is applied to the unsteady prediction of turbulent flow field, Achieve the feasibility of inlet start. The results show that the plate shock / turbulent boundary layer disturbance (STBLI) problem and the LES method can clearly and reliably predict the reflection and separation shocks and the mutual interference between the shock wave and the fully developed turbulent boundary layer. The quantitative results are consistent with the experimental results. In the aspect of airway research, under the condition of laminar flow, the shock wave is strongly separated, leading to the blockage of the air intake. However, the test and calculation after turbulence control show that the flow field separation is obviously reduced, the flow field is stable and no obvious blockage, The inlet port can be started and the total pressure recovery coefficient meets the requirements. The results show that it is feasible to use the strong turbulence to weaken the separation and realize the intake port start-up.