Flow Behavior in Side-View Plane of Pitching Delta Wing

Abstract

In the present investigation, a delta wing which has 70° sweep angle, Λ was oscillated on its midcord according to the equation of α(t)=α m +α o sin(ω 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, β over a slender delta wing. The value of mean angle of attack, α m was taken as 25°. The yaw angle, β was varied with an interval of 4° over the range of 0°≤β≤ 16°. 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 α o =±5°.Formations and locations of vortex breakdown were investigated by using the dye visualization technique in side view plane.