摘要
本文利用二阶线化理论对当地流活塞理论作了修正 ,利用激波脱体的临界折角确定翼型上声速线位置 ,并用插值法估计脱体激波到声速线之间局部亚音速区的当地气流参数 ,声速线后的当地气流参数仍由膨胀波公式计算 ,从而形成了适合于激波脱体流态的小展弦比大迎角翼面颤振工程估算的一整套方法。如考虑翼前缘圆角的存在 ,全部Mn >1的小展弦翼面都可用本文方法统一进行颤振分析。经Ma =1.1～ 2 .5的带迎角舵模型风洞颤振试验验证 ,表明本文方法具有一定的精度 ,能满足工程设计要求。
In the paper a new engineering approximation is presented for high attak angle flutter analysis and a flutter calculation approach is available for small aspect ratio wing with high attack angle and bow shock wave on leading edge.In the new method,the local flow piston theory is amended by second_order linearization theory,the position of the sonic_line on airfoil is determined by the critical angle of generating bow wava and the local flow parameter can be estimated on the local subsonic extent by interpolation.The local flow parameter after the sonic_line can yet be calcuated by the shock_expansion method.Thanks to existence of round corners the flutter analysis can be consolidated for small aspect ratio wing of M n>1.The results from numerical example and M a=1.1～2.5 wind_tunnel flutter experiments show that the method is effective and of practical value for engineering application.
出处
《振动与冲击》
EI
CSCD
北大核心
2002年第4期100-103,共4页
Journal of Vibration and Shock
基金
航天工业总分司"九五"预先研究重点项目 (2 2 .9.1 /A960 0 0 8- 1 2 )
