Flow Behavior in Side-View Plane of Pitching Delta Wing

In the present investigation, a delta wing which has 70 degrees sweep angle,. was oscillated on its mid-cord according to the equation of alpha(t)=alpha(m)+alpha(o)sin(omega(e)t). This study focused on understanding the effect of pitching and characterizing the interaction of vortex breakdown with oscillating leading edges under different yaw angles, beta over a slender delta wing. The value of mean angle of attack, am was taken as 25 degrees. The yaw angle, beta was varied with an interval of 4 degrees over the range of 0 degrees <=ss <= 16 degrees. The delta wing was sinusoidally pitched within the range of period of time 5s <= T-e <= 60s and reduced frequency was set as K=0.16, 0.25, 0.49, 1.96 and lastly amplitude of pitching motion was arranged as alpha(o)=+/- 5 degrees. Formations and locations of vortex breakdown were investigated by using the dye visualization technique in side view plane.