飞机机身腹部与两侧进气道性能比较试验研究

通过高低速风洞试验,对比迎角和侧滑角对机身腹部和机身两侧进气的进气道气动性能的影响。试验结果表明:在超音速来流状态下,当迎角增加到5°时,腹部进气道的气动性能改善,而两侧进气道的气动性能几乎不变;在亚音速来流状态下,当迎角从6°逐渐增加到所试验的值(高亚音速为12°,低速为30°),两侧进气道的气动性能逐渐明显变差,而腹部进气道的气动性能对迎角并不敏感,基本能保持无迎角时的性能;在高低速来流状态下,两种型式进气道的气动性能对所试验的侧滑角β(小于6°或9°)均不敏感。 

Comparision of Inlet Performance with the underfuselage Inlet and Fuselage Side Inlets

This thesis compares the influence of the angles of attack (α) and yaw (β) on the inlet performance with the underfuselage inlet and the fuselage side inlets by means of low and high speed wind tunnel tests.The results show that in supersonic flow the aerodynamic performance of the underfuselage inlet becomes better when the angle of attack changes from 0 to 5°,but that of the fuselage side inlets remains almost unchanging.In subsonic flow when the angle of attack changes from 6° to 12° (high subsonic) or 30° (low speed),the performance of the fuselage side inlets becomes worse obviously,but that of the underfuselage inlet almost does not change with the angle of attack and can be kept the same as α=0°.In high and low speed free stream flow,the performance of two kinds of inlets almost does not change with β.