气动格栅改善进气道流场的实验研究

AN EXPERIMENTAL INVESTIGATION OF THE INLET EXIT FLOW FIELD IMPROVED BY AERODYNAMIC GRID

关键词:  超音速送气道  流场畸变  改进

Key words:  Supersonic inlet  Flow distortion  Improvement

摘要:

对一种能有效改善管流出口流场的新型整流装置——气动格栅(下称格栅)作了介绍。在超音速冲压发动机进气道下游进行了格栅与网格的对比实验研究,得到了大超临界工况下,格栅比网格具有更好的整流效果:在马赫数1.8、攻角为零度时,格栅出口气流总压畸变指数D比网格低约50％。

Abstract:

A new type device, aerodynamic grid, is introduced to uniform the flow field at the duct exit.Experimental investigation of both aerodynamic grid and wire screen mounted at the downstream of ramjet inlet has been conducted and comparison of the experimental results has been made.The results of investigation show that the effect of aerodynamic grid on the flow field is better than that of wire screen under inlet supercritical condition.At the Ma∞= 1.8 and zero angle of attack of the inlet, the total pressure distortion of flow, D, at aerodynamic grid exit can be reduced by 50% as compared with that of flow at wire screen exit.