Numerical Simulation of the Flow Around a Light Aircraft Wing

Abstract

This work aims to study and simulate the behavior of flow over SAFAT-01's wing using numerical simulation based on solving Reynolds's Averaged Navier-Stokes equations coupled with K-ω turbulent model. The wing model is simple rectangular with elliptical ends. In the present work, aerodynamics characteristics and different flow phenomena were predicted at different design conditions (e.g. at different angles of attack) and at Re=5.2×10 6 . The present study analysis the vortices which occur over wing and captured their effective regions at critical design conditions. This study indicates that the maximum lift coefficient for SAFAT-01's wing is 1.44 occurred at stall angle of attack 12 o , maximum lift to drag ratio (L/D) is 26 which occurs at -4 o , and the zero lift drag coefficient is 0.0142. To validate this numerical simulation, a typical wing which found in Ref. [3] was analyzed, a comparison between predicted results and available results indicate that this numerical simulation has high ability for predicting the aerodynamics characteristics.