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为了对超声速进气道内激波/边界层干扰控制进行研究,将进气道简化为平板/楔形体结构,用数值方法研究一段包线上吹除法抑制气流分离的性能变化趋势以及吹除气体总压、喷嘴高度对吹除性能的影响。研究表明,吹除法在一定马赫数范围内能抑制气流分离,马赫数超过设计点后,随着马赫数增大吹除性能降低。达到吹除效果后增大吹除压力和增加喷嘴高度不能提高吹除性能。随着来流马赫数增大,气流抗反压能力增强,气流分离减少。
In order to study the control of shock wave / boundary layer in the supersonic inlet, the inlet is simplified as a flat plate / wedge structure. The numerical method was used to study the trend of the performance of the gas flow separation in a section of the line, Pressure, nozzle height on the blowing performance. The results show that the blow-off method can suppress the air-flow separation within a certain Mach range. After the Mach number exceeds the design point, the blow-off performance decreases as the Mach number increases. After the blow-off effect is achieved, the blow-off pressure is increased and the height of the nozzle is increased, so that the blow-off performance can not be improved. As Mach Mach number increases, airflow anti-back pressure capability increases, reducing airflow separation.