Parametric study of sweeping corrugated wing and role of spanwise flow in delayed stall

Abstract

The present study identifies the effect of different parameters like angle of attack, acceleration duration, aspect ratio and taper ratio on a corrugated wing in sweeping motion at Re 34000. Moreover, the role of spanwise flow on delayed stall is also analyzed. This study will help in identifying the suitable parameters for the wing of MAV. Calculations are performed at constant angle of attack of 10°, 20°, 30° and 40°; acceleration duration of 10°, 20° and 30°; aspect ration of 3, 4.5 and 6 and taper ratio of 0.5, 0.75 and 1. In order to analyze the spanwise flow, velocity was calculated on the wing at different chord lengths. Results indicated that C <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">l</sub> and C <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">d</sub> increased with the increase in angle of attack and leading edge vortex was more prominent achieved as a result of delayed stall at later stage of sweeping motion was independent of initial acceleration duration. The variation of aspect ratio had minor effects on aerodynamic force production. The values of C <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">1</sub> and C <sub xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">d</sub> increased with the increase in taper ratio and purely rectangular wing produced better results. The velocity vectors confirmed the presence of spanwise velocity on the wing at leading edge vortex core. This velocity initially increased and attained the maximum value close to mid-span and this value was larger than the chordwise velocity corresponding to Re under investigation.