三角翼俯仰振荡中若干参数影响的实验研究  

An Experimental Investigation about the Effect of Some Parameters on the Unsteady Aerodynamic Characteristics for a Delta Wing during Pitching Oscillation

作　　者：秦燕华[1] 黄军辉[1] 

机构地区：[1]北京航空航天大学,北京100083

出　　处：《空气动力学学报》2000年第3期315-323,共9页Acta Aerodynamica Sinica

基　　金：国防科技预研基金

摘　　要：本文研究一个 6 0°三角翼以不同振荡频率 ,不同振幅从不同起始迎角进行俯仰振荡的纵向气动力特性 ,研究发现跨越具有不同时间尺度的流态的振荡会产生明显的气动力迟滞现象 ,这一迟滞现象随减缩频率的增大有一个极限值 ;在同一种流态下振荡 ,气动力迟滞现象不明显 ,这一结果对充分利用非定常气动力有指导意义。The effect of reduced frequency, amplitude and starting angles of attack during the pitching oscillation on the unsteady aerodynamic characteristics of a delta wing with 60 degree swept has been studied in a low speed wind tunnel. It is found that the obvious aerodynamic hysteresis loop will arise when the pitching oscillation of the model goes through the different flow condition with different time scale and the size of aerodynamic hysteresis loop is limited with the reduced frequency increased. It is also found that the aerodynamic hysteresis phenomena are not significant when the pitching oscillation goes only through the same flow condition. Consequently the results are useful to the application of unsteady aerodynamic forces.

关 键 词：非定常空气动力学 三角翼 俯仰振荡 迟滞现象 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]