边条翼和近距鸭翼布局模型动态气动特性分析

摘要

针对边条翼与近距鸭翼这两类典型战斗机布局模型，在中国空气动力研究与发展中心 FL—24风洞进行了大振幅俯仰动态试验与模型自由摇滚试验，并对比分析了边条翼与近距鸭翼布局模型高速大迎角的动态气动特性。结果表明：边条翼模型纵向动态特性明显优于近距鸭翼模型，尤其是俯仰力矩迟滞效应更强；近距鸭翼模型在攻角26°～45°区间出现了较大的滚转力矩，容易诱发摇滚运动；最后，通过自由摇滚试验验证了俯仰动态试验分析结论，即近距鸭翼模型在迎角大于30°后出现了极限环摇滚现象。%The pitching oscillation with large amplitude dynamic test and free—to—roll test on two typical fighter configuration models of hinged strake—wing and close—coupled wing—canard are conducted in FL—24 wind tunnel of China Aerodynamic Research and Development Center (CARDC).An analysis of the dynamic aerodynamic characteristics of hinged strake—wing model and close—coupled wing—canard configuration is made at high angles of attack.The results show that the longitudinal dynamic characteristic of hinged strake—wing model is obviously better than that of the close—coupled wing—canard model.Especially,the pitching moment hysteresis effect of hinged strake—wing model is stronger.Meanwhile,the roll moment of canard wing model is large at the range of attack angles from 26°to 45°.It means that close—coupled wing—canard model is in—duced rock more easily.Finally free—to—roll experiment is carried on.The experiment results show the limit cycle rock phenomenon of the canard model appears in the angle of attack greater than 30°degrees,so the analysis conclusions of the longitudinal dynamic test have been validated.