In this research, viscous, laminar and steady flow around symmetric and non-symmetric airfoils is simulated in the presence of heat transfer. Navier-Stokes (N-S) equations are discretized by Finite Volume Method (FVM) and are solved by SIMPLE algorithm in open source software, OPENFOAM. The main objective of this paper is introducing thermal camber phenomenon which can improve aerodynamic performances. Actually, a symmetric airfoil like NACA0012 with thermal camber is compared with the airfoils with physical camber including NACA2412 and NACA4412 to specify which type of these cambers has more effects on aerodynamic efficiency. Furthermore, various temperatures are tested in order to find optimum condition. After validation, results indicated that cooling upper surface and heating lower surface of symmetric airfoils which are named thermal camber cause lift generation and improve aerodynamic performances at zero Angle of Attack (AOA). These improvements can be more than of airfoils with physical camber in the same condition which can prove excellence of thermal camber than physical one. Also by applying thermal camber on NACA2412 and NACA4412 airfoils, lift to drag coefficient ratio increases more than of conditions with only cooling or heating the surfaces.

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