摘要
为了研究战斗机的机翼摇滚特性 ,运用风洞试验和数值模拟手段 ,对一典型三角翼布局开展了研究工作。风洞试验研究探讨了不同攻角和初始角位移等因素对机翼摇滚特性的影响 ;运用非定常建模技术建立了机翼摇滚过程中的滚转力矩系数的表达式并进行了机翼摇滚的数值模拟 ,预测了发生机翼摇滚的临界攻角和轴承阻尼系数对摇滚特性的影响。最后对机翼摇滚的发展、稳定阶段的能量转换进行了讨论。研究结果表明机翼摇滚的数值模拟与试验结果具有较好的一致性。
In order to study the wing rock characteristics of a fighter,the wing rock characteristics for a fighter with delta wing configuration is investigated in this paper. The experimental research about the effects of angle of attack and initial roll angle on wing rock characteristics are conducted in 4m×3m low speed wind tunnel. On the other hand, the critical angle of attack and the effect of different friction of ball bearing on wing rock were predicted by using numerical simulation based on the unsteady rolling moment modeling. In addition, the energy exchange during the developing and steady period of wing rock is also discussed. The results indicate that the numerical simulation is in good agreement with the experiment.
出处
《流体力学实验与测量》
CSCD
北大核心
2002年第3期1-7,共7页
Experiments and Measurements in Fluid Mechanics
关键词
战斗机
机翼
摇滚特性
风洞试验
数值模拟
high angle of attack
wing rock
wind tunnel test
numerical simulation
