高超声速流动的气体吹除控制方法研究

Study on Air Blowing Control Method for Hypersonic Flow

为了在超燃冲压发动机直连式试验台上得到真实的非均匀试验气流,采用商业软件Fluent对高超声速流动的气体吹除控制进行了数值研究。在试验台喷管和发动机隔离段之间增加了吹除控制段,试验了4种吹除方案。常温空气从位于控制段顶部、侧部和底部的吹除口注入,吹除口包括长槽、短槽和圆孔等,吹除气体的流量为来流流量的8.3%~13.3%。以超燃冲压发动机自由射流计算结果为基准,比较分析了控制段出口截面马赫数分布。结果表明,"顶槽"方案能够得到较为理想的吹除效果,吹除参数优化后可为试验提供指导。

A computational study on the air blowing control method for hypersonic flow was conducted by CFD simulation with software Fluent to maintain practical non-uniform test inflow in the scramjet direct-connect wind tunnel. A blowing control section was placed between facility nozzle and isolator. Ambient air was injected into control section from its upper, side and lower blowing orifice or slot （long/short） . Four different blowing schemes were tested. The mass fluxes of blowing air were about 8.3% - 13.3% of inflow. The free-jet computation- al result of scramjet model were taken as the bench mark for comparison and analysis. According to the Maeh numbers distribution at control section exit, the ＇upper slot＇ scheme was figured out as the best one. These re- suits could be a guide for experimental research after parameters optimization.