三次元基本形状模型のダイナミックリフト風洞試験

揚力測定及び可視化試験

抄録

The aerodynamic force and PIV (Particle Image Velocimetry) measurements over the wing of a 3-D basic model in pitching motion were conducted in MHI Nagoya's low speed wind tunnel to investigate the dynamic lift and vortex behaviors. In this paper, experimental results of some wings on the various pitch rate conditions are shown. The dynamic effect begins to appear on the high angle of attack because the dynamic vortex is formed and prevents the separation. At that time, the sweepback angle of the wing is the main parameter to maximize the dynamic effect. And the dynamic vortex distribution analyzed from the PIV measurement results shows the followings. The dynamic vortex sheds over the wing from the wing root leading edge to the wing tip trailing edge and starts to break down instantly after the pitching motion is stopped. Moreover by comparing the dynamic vorticity with the dynamic lift, it is turned out that both have a close correlation.