مشخصات پژوهش

In this paper, the effects of heat flux on the aerodynamics coefficients NACA0012 wing section were studied. The subsonic turbulent flow was simulated primarily by using two different methods of turbulence modeling in low angle of attacks and then was compared with experimental results. Finally Reynolds Stresses method was selected as a proper technique. Upper and lower surfaces of airfoil are divided into ten equal elements, and then the flow over the airfoil was simulated by choosing eight elements of the airfoils’ upper surfaces and different heating fluxes values. The results indicated that how much the applied heat flux was closer to the airfoil trailing edge while the heat flux had the most efficacies on the drag reduction and the lift coefficient increment. Eventually, according to the results, optimal surface for applying the heat flux was close to the trailing edge and optimum thermal flux was equal to 7500 w/m 2 .