NUMERICAL SIMULATION OF THE FLOW AROUND A LIGHT AIRCRAFT WING

Document Type : Original Article

Authors

1 Assoc. professor, Dept. of Aeronautics, Karary University, Omdurman, Sudan.

2 M. Sc. student, Dept. of Aeronautics, Airframe Design, Karary University, Omdurman, Sudan.

3 Assistant Professor, Aeronautics Eng. Dpt., Sudan University of Science and Technology, Khartoum, Sudan.

Abstract

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- 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=5.2×106. 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 12o, 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.

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