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在西德宇航院跨音速风洞(TWB)进行的翼型油流实验结果表明,传统的关于侧壁效应的概念和理论只能适用于亚临界流动。超临界情况下,侧壁效应现象更复杂,影响更严重。实验中观察到的流油谱可分为五类。油流谱的发展规律说明侧壁干扰主要来源于侧壁边界层的位移效应。实侧壁“二元风洞”对跨音速翼型实验不能模拟真实情况。油流照片表明,即使风洞宽度达到翼型弦长的3.4倍,侧壁对中心截面的流动仍会有明显影响,侧壁抽气技术作为克服侧壁效应的手段是很有希望的。
The experimental results of airfoil oil flow at Transonic Wind Tunnel (TWB) at Sidley Aerospace show that the traditional concept and theory of sidewall effect can only be applied to subcritical flow. Under supercritical conditions, the phenomenon of sidewall effects is more complicated and the impact is more serious. The observed oil flow spectrum can be divided into five categories. The development of oil flow spectrum shows that the side wall disturbance mainly comes from the displacement effect of the side wall boundary layer. Real sidewall “dual wind tunnel” on the transonic airfoil experiment can not simulate the real situation. The oil flow photos show that sidewall flow can have a significant effect on the cross section flow even though the width of the wind tunnel reaches 3.4 times the chord length of the airfoil. Side wall pumping is promising as a means of overcoming the sidewall effect.