三角翼动态气动特性低速实验研究

Low Speed Experimental Investigation on the Unsteady Aerodynamic Characteristics for Delta Wings

三角翼快速上仰和正弦振荡非定常气动力的实验研究是在西北工业大学Φ1．5m开口、低速风洞中进行的。60°三角翼迎角从0°到90°的快速上仰实验结果表明，随上仰速率的提高，最大升力系数和失速迎角随之增大。本文还对大振幅正弦振荡三角翼的减缩频率，平均迎角，振幅和俯仰轴位置对机翼瞬态载荷的影响进行了研究。

The experimental investigations of unsteady aerodynamic characteristics of rapid pitch and oscillating for delta wings of high incidence were carried out at 1.5m open-jet, low speed wind tunnel of NPU.The experimental results show that the maximum dynamic lift coefficients and stall incidence campared to steady state values were increased with the increase of rate of pitched when the 60°delta wing in rapidly pitching up at incidence from 0°to 90°. The influence of reducefrequency, mean angle of attack, amplitude and pitch axis location of oscillating wings on the transient load were researched.