In this paper, NACA 0015 airfoil was studied. focusing on the pressure Distribution, lift and drag forces. Changing of the ground clearance was Considered, too. Meanwhile, the angle of attack was changed from 0 to 10. Pressure coefficient reached a higher amount on the wing lower surface when the ground clearance diminished. Increment of the angle of attack led to outspread of the high pressure domain over the lower surface and so led to greater lift force. For higher angles of attack, the ground clearance had no effect on the pressure distribution. Mostly for high angles of attack, the suction effect on the upper surface made an adverse pressure gradient which could cause turbulent behavior and finally enhanced the drag force. To solve the problem, the SIMPLE algorithm was utilized. Moreover, the QUICK algorithm and second-order upwind were used for momentum verification and turbulent viscosity, respectively. Finally, the efficiency of the utilized model was checked. It was observed that unlike the Spalart-Allmaras, the k - ɛ model cannot give acceptable results admitting experimental data. This matter is depicted for drag and lift coefficients and also the pressure distribution on both surfaces of the airfoil.
کلید واژگان :Airfoil;Llift;Ddrag;Ppressure coefficient; Spalart-Allmaras
ارزش ریالی : 350000 ریال
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