旋转导弹Gurney襟翼尾翼气动特性研究

Aerodynamic Research on Tail with Gurney Flap of Spinning Missile

对某旋转导弹加装Gurney襟翼的尾翼气动特性进行了研究。基于该导弹气动外形,将产生滚转力矩的斜置尾翼改为加装Gurney襟翼的平置尾翼。建立了计算模型,不同外形、马赫数和攻角条件下的数值计算表明:增加Gurney襟翼的尾翼增加了导弹的滚转力矩,同时也增大了阻力,降低了升阻比。合理选择Gurney襟翼的偏折展弦长和偏折角度,可在保证升阻比和全弹压心变化不大的条件下,改善导弹亚跨段转速特性。风洞试验结果验证了数值计算结果的正确性。

The aerodynamic of tail with Gurney flap of some spinning missile was studied in this paper.The computation mode was established.The results of numerical simulation under various configuration,Mach and angle of attack showed that the tail with Gurney flap would increase the missile rolling moment and missile drag and decrease the lift to drag ratio.By choosing an appropriate deflection chord and angle to make little change for the lift to drag ratio and pressure center coefficient,the missile rolling speed characteristics of subsonic and transonic time would be improved.The numerical simulation was validated by wind tunnel test.