大型民机巡航状态下头部流动特性实验研究

The experimental study of large civil aircraft nose flow characteristics in the cruising condition

高速巡航飞行时,机头的流动特性对大型民机的耗油率以及驾驶舱的舒适程度都有影响,民机高速巡航飞行时要求飞机头部尽可能不存在分离流动,高速气流在机头舷窗位置不出现激波。通过风洞试验,在FD-12高速风洞中得到了某民机头部的压力分布、彩色油流照片以及PIV空间流场显示结果。试验结果表明:在巡航状态下,机头表面主要是附着流动,来流马赫数为0.82时,机头舷窗后方局部出现超声速区。

The nose flow characteristics on large civil aircraft have such a significant influence on the fuel consumption and comfort of pilot compartment that the absence of flow separation zone near the nose and shock wave on the porthole is required in the cruising condition with a high flight velocity. This paper obtains pressure distributions, oil flow pattern and PIV result by the wind tunnel test. Experimental results showed that at small angle of attack, the nose flow is atta ched in the cruising condition, and when Ma=0. 82, a supersonic region emerges at the rear of porthole.