关键词: 超音速送气道;流场畸变;改进

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.

Key words: Supersonic inlet;Flow distortion;Improvement