CAJ | 학술논문

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。
통과재림계뢰낙수범위내적익신조합체자유요곤시험，개전료전체와우동대궤익요곤적류동공제연구。실험결과표명，통과대전체와적공제가이유효소제익신조합체요곤적발생，첨가두첨우동적위치대공제효과구유명현영향，우동재정측향공제효과최가，저충요곤공제방식재교관적영각범위급마혁수범위내균유효。대전체와유도궤익요곤적우동공제궤리주료간요분석。
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°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×0.6m section of transonic wind tunnel of CARDC.The encoder with the resolution of 0.088°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°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.