前体涡诱导机翼摇滚扰动控制高速风洞试验研究

通过在临界雷诺数范围内的翼身组合体自由摇滚试验，开展了前体涡扰动对机翼摇滚的流动控制研究。实验结果表明，通过对前体涡的控制可以有效消除翼身组合体摇滚的发生，添加头尖扰动的位置对控制效果具有明显影响，扰动在正侧向控制效果最佳，这种摇滚控制方式在较宽的迎角范围及马赫数范围内均有效。对前体涡诱导机翼摇滚的扰动控制机理做了简要分析。

Flow control investigation on wing rock induced by forebody vortex at high speed wind tunnel

The wing rock phenomenon induced by forebody asymmetric vortices is likely to oc-cur on modern aircrafts with slender forebody flying at large angles of attack.Over a model of a pointed ogive-cylindrical body with 30＆#176;swept wing at the fixed angles of attack in the wind-tun-nel,the effect of artificial perturbation’s location around the nose tip is studied through the free to roll test in the critical Reynolds numbers range.The test apparatus and test methods as well as data acquisition were presented too.The experiments are conducted in the 0.6m＆#215;0.6m section of transonic wind tunnel of CARDC.The encoder with the resolution of 0.088＆#176;which is coupled with the rotor is employed to record the free to roll motion.High precision mechanical bearings are used to minimize the friction in free to roll experiments.A spherical particle with the diameter of 0.2mm which is attached onto the rotatable tip of the model is as the artificial perturbation.Based on various type of experiments of forebody asymmetric vortices that influence the wing rock motion over the slender body with 30＆#176;swept regular wing,the relationships between tip perturbation and roll-ing oscillation induced by different types of forebody asymmetric vortices are studied.As the test result indicated,the manual perturbation on the nose tip could prevent the wing rock remarkably when it was placed on side direction and the control effect work on a wide range of attack and Mach numbers.The wing rock flow control mechanics are briefly analyzed too.