小展弦比飞翼高速大攻角下横航向气动力散布分析

Investigation of Lateral-Directional Aerodynamics Scatter for Low Aspect Ratio Flying Wing Configuration at High Speed and High Angle of Attack Conditions

为了深入分析小展弦比飞翼布局气动力特性,采用了风洞试验方法对一种小展弦比飞翼布局开展了静态测力试验研究,得到了该模型的基本气动力特性。试验研究结果表明,在多次重复性试验条件下,横航向气动力出现较大的散布,其中,Ma=0.8,散布区域攻角变化范围为α=12°~28°;Ma=0.95,散布区域攻角变化范围为α=8°~16°;Ma=1.5,散布区域攻角变化范围为α=14°~16°。在重复性试验中出现这种测试值的散布,表明在该试验条件下,气动力具有明显的不确定性;在这些飞行条件下小展弦比飞翼布局可能出现横航向失稳运动。

In order to investigate the aerodynamic characters of low aspect ratio flying wing configuration,conventional static force and moment test was conducted in wind tunnel and the basic aerodynamic characters were attained.The result revealed that large data scatter existed for lateral-directional aerodynamics in repeat runs.The scatter regions are Ma=0.95 and at Ma=1.5 when the range of attack angle Ma=0.8.These phenomena indicated that there was obvious extent of uncertainty for lateral-directional aerodynamics at these conditions.We speculated that lateral-directional destabilizing motions may occur for this low aspect ratio flying wing configuration at these flight conditions.