飞机机身大迎角气动力实验研究

Experimental Study of Aircraft Fuselage Aerodynamic Forces at High Angles of Attack

本文研究了机身模型在迎角０～９０°范围内的气动特性，实验风速为２１ｍ／ｓ，相应的实验雷诺数（基于机身直径）为０．８６×１０５。模型可改变前体头部形状、前体形状、前体长细比和后体长细比，以研究机身形状和几何参数对气动特性的影响。重点分析了非对称起始迎角、侧力和偏航力矩特性。本文研究的机身形状包括尖切拱形、圆锥、钝头型圆锥、椭圆锥和鲨形等５种前体以及相应的后体：所讨论的几何参数有头部半顶角、前体长细比、前体椭圆厚度比以及后体长细比。通过实验发现：侧力起始迎角主要由前体头部的几何特征来控制，同时前体形状的变化对机身非对称侧力的形成，发展起重要作用。

A series of low speed aerodynamic force tests on generic aircraft fuselage models were carried out over the angle of attack(AOA)range of 0￣90°at Reynolds number, Red= 0 .86×105 (formed with the fuselage diameter). The models tested consist of different nose shapes,forebody shapes, forebody fineness ratios and afterbody fineness ratios to study the effects of fuselage shapes and geometrical parameters on aerodynamic forces. The angle of attack where side force first occurs (aonset),side force and yawing moment are examined in detail. Fuselage shapes include tangent ogive, cone, blunted cone, elliptical cone and shark configuration. The geometrical parameters discussed involve nose semiapex angle, forebody fineness ratio, forebody elliptical thickness ratio and afterbody fineness ratio. It was found in this experiment that the side force onset AOA is mainly dominated by nose geometry characteristics and the variations of forebody shapes have important effects on the formation and development of asymmetric side force.