实体鼓包改进超临界翼型跨声速气动特性研究

采用风洞试验手段,初步研究了高速试验条件下二元翼型加载的实体鼓包高度、形状、安装位置等多方面因素对其减阻特性的影响,结果表明,实体鼓包可以减小阻力系数,在某些特定情况下(一般为中高升力系数情况下)可明显提高升阻比;实体鼓包的最佳应用场合是中高升力系数情况,小升力系数情况下不宜采用实体鼓包,如采用,则应使用较小的最大高度。为充分发挥实体鼓包的减阻作用,并且不至于因此导致气动性能的下降,最佳方法是采用自适应实体鼓包,根据需要随时改变其位置和高度。

Investigation on drag reduction with contour bump located on a supercritical airfoil

Various experimental methods including force,velocity and pressure measurements in wind tunnels are applied on two-dimensional airfoils to investigate the drag-reduction effects of contour bump at different heights,shapes,mounting locations under high speed conditions,and the mechanism of drag reduction is also further analyzed.The results of drag-reduction characteristics show that the contour bump reduces the drag coefficient,and at some certain conditions(such as moderate-to-high lift coefficient conditions) increases the lift-to-drag ratio remarkably.The best conditions for contour bump application are at moderate-to-high lift coefficient conditions while not at low lift coefficient conditions,If the contour bump is adopted at low lift coefficient conditions,its height should be reduced.In order to fully utilize the contour bump and to eliminate its defects,a contour bump which can move up/down and vary its height and location is strongly suggested.