Abstract
In this research, viscous, laminar and steady flow around symmetric and non-symmetric airfoils is simulated at Low Reynolds Number (LRN). Navier-Stokes (N-S) equations are discretized by Finite Volume Method (FVM) and are solved by the SIMPLE algorithm in an open source software, namely OpenFOAM. The main objective of this paper is the introduction of the thermal camber phenomenon. This phenomenon is used to improve the aerodynamic performance. Hence, a symmetric airfoil, like NACA0012, with thermal camber is compared with the airfoils with the physical camber, including NACA2412 and NACA4412, to specify which camber type has more effects on the aerodynamic efficiency. Furthermore, various temperatures are tested in order to find the optimum condition. After validation, results indicated that cooling upper surface and heating lower surface, namely thermal camber, generate lift force and improve aerodynamic performance for symmetric airfoils at a 0° Angle of Attack (AOA). These improvements are more than the airfoils with physical camber. Also, when this method is applied to the NACA2412 and NACA4412 airfoils, lift to drag coefficient ratio will increase more than the condition with only cooling or heating the surfaces.
Highlights
Due to the importance of Micro Aerial Vehicles (MAV), many studies have been done to develop this field of research
The motivation of recent attempts is to improve the aerodynamic performance in Low Reynolds Number (LRN) flows
The theory of using heat transfer based on the viscous boundary layer characteristics can be utilized to improve the aerodynamic efficiency
Summary
Due to the importance of Micro Aerial Vehicles (MAV), many studies have been done to develop this field of research. The motivation of recent attempts is to improve the aerodynamic performance in Low Reynolds Number (LRN) flows. In this range of Re, the adverse pressure gradient plays a destructive role in aerodynamic performance and causes flow separation over the airfoil. The separation happens either at leading edge or trailing edge. This separation increases the drag and reduces the lift (Febi Ponwin and Rajkumar 2015). Many methods, including optimization of airfoil shape, blowing and suction, have been used in those studies to overcome mentioned problems. Thermal effects on the flow can be clarified by investigation of the airfoils in steady conditions.
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