In the context of the wing–fuselage junction flow the purpose of a nose-fairing is to prevent the oncoming boundary-layer flow separation, which in turn eliminates the horseshoe vortex formation at the junction. A simple procedure is proposed here to arrive at an asymmetric fairing shape for a non-zero wing incidence angle. Even though it is a simple method to decide on fairing shape and size, the fairing designed by this method for a wing at 4° incidence is shown to satisfy the purpose of the nose-fairing. The wind tunnel experimental results clearly show that the designed fairing improves the flow quality at the wing–body intersection by preventing flow separation and vortex formation. Relatively lower momentum deficit in the boundary-layer (behind the wing trailing edge) hints at drag-reduction for the faired configuration.

在机翼-机身交汇处，流鼻水的目的是防止即将到来的边界层流动分离，从而消除交汇处的马蹄涡流。在此提出一种简单的程序，以实现非零机翼入射角的不对称整流罩形状。尽管确定整流罩的形状和尺寸是一种简单的方法，但通过这种方法为4°入射角的机翼设计的整流罩仍然可以满足机头整流罩的目的。风洞实验结果清楚地表明，设计的整流罩可通过防止流分离和涡流形成来改善机翼与机体交叉处的流动质量。边界层中（在机翼后缘之后）相对较低的动量赤字暗示了整流罩构型的减阻。