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进气道抽吸区域一般包含大量抽吸孔,这些抽吸孔的网格前处理异常繁复、离散求解及CFD仿真困难。为避免这些问题,利用集成了渗透边界模型的数值仿真软件AHL3D模拟小孔抽吸,获得了小孔抽吸对三维内转式进气道Ma4~6内的启动性能的影响。结果表明:同等条件下,渗透边界与抽吸孔仿真的机体侧壁面压力曲线基本重合,且进气道喉部参数最大差别小于1.5%,说明利用渗透边界模型研究抽吸对进气道启动性能的影响具有可行性;边界层抽吸位于分离泡最高压力点附近时,可实现进气道宽马赫数范围(Ma4~5.5)的启动;Ma5条件下,开孔率在0.1左右,进气道实现启动,且启动后流量抽吸率低于1%;抽吸背压为6.5倍来流静压时,进气道实现启动,启动后流量损失几乎为0,压力分布规律与远场初始化得到的启动流场完全一致。
Inlet suction area generally contains a large number of suction holes, these suction holes mesh pretreatment exception complex, discrete solution and CFD simulation difficult. In order to avoid these problems, numerical simulation software AHL3D integrating penetration boundary model was used to simulate orifice suction, and the influence of orifice suction on the start-up performance of three-dimensional inner transitional inlet Ma4-6 was obtained. The results show that under the same conditions, the pressure curves of the side wall surface of the permeating boundary and the suction hole are basically coincident, and the maximum difference of the throat parameters of the inlet port is less than 1.5%. This shows that using the percolation boundary model, The effect of boundary layer suction is feasible when the boundary layer suction is near the maximum pressure point of the separation bubble, and the start of the wide inlet Mach number range (Ma4-5.5) can be achieved. In Ma5, the porosity is about 0.1, And the flow suction rate is less than 1% after start-up; when the suction back pressure is 6.5 times the flow pressure, the inlet port is started up and the flow loss after start-up is almost zero. The pressure distribution and the initializing of the far field are obtained The starting flow field is exactly the same.