Determination of operating point for a propulsive wing UAV using CFD

Abstract

This report seeks to determine the operating point of a 2D propulsive wing UAV using CFD. CFD simulations were performed using a 2D RANS k-ε turbulence model and the rotating flow was captured using the moving reference frame method. Lift and drag were obtained for different angle of attacks via a control volume analysis of CFD results. This was done to eliminate ambiguity as compared to a conventional approach where forces were obtained by performing force integrations on lifting surfaces. Wind tunnel tests were then conducted on a 3D printed propulsive wing model to assess and confirm the general trends produced by CFD. Both CFD and wind tunnel test displayed improvements in lift and showed good agreement with literature. In addition, contour plots of CFD showed wake filling effect of the cross flow fan. General trends for operating points in CFD agrees with that obtained by wind tunnel testing.