Flow Behavior in Side-View Plane of Pitching Delta Wing

¹ Department of Mechanical Engineering, Faculty of Engineering and Architecture, Cukurova University, 01330, Adana / Turkey
² Departments of Aerospace Engineering, Faculty of Aeronautics and Aerospace, Gaziantep University, 27310, Gaziantep / Turkey

^* Corresponding author: bsahin@cu.edu.tr

Published online: 4 June 2018

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+α₀sin(ω_et). 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 α₀=±5°.Formations and locations of vortex breakdown were investigated by using the dye visualization technique in side view plane.