COMPARATIVE NUMERICAL ANALYSIS OF HIGH LIFT AIRFOILS AND EFFECT OF MACH NUMBERS USING CFD

Aravind Satheesh Kumar, Tarun Yadav, Bharat Singh Mandloi, RP Khapli

Abstract: This paper focuses on the comparative numerical analysis of two high lift airfoil’s geometries using Computational Fluid Dynamics. Two airfoil’s MDA30P30N and S1223RTL were chosen for the analysis at various angle of attack. Three Mach Numbers mainly 0.2M, 0.6M and 0.8M were considered for the analysis. The simulations were carried out at atmospheric conditions similar to an altitude of 40,000ft, which is the altitude used commonly by aviation airplanes for cruising. The flow features like pressure variation, velocity distribution, turbulent viscosity variation, streamline distribution and eddy loop formations along with aerodynamic coefficients like Coefficients of Lift and Drag were studied and analyzed. The CFD results of MDA30P30N was validated with the experimental results. It is concluded that multi element airfoil MDA30P30N gives better aerodynamic performance than single element airfoil S1223RTL. Hence, it is prudent to use multi-element airfoils than single element high lift generating airfoils in general aviation aircraft.

Keywords: Aerodynamics, Computational Fluid Dynamics (CFD), Drag coefficient, Mach number, Multi-element, High-lift devices, Airfoil, Lift coefficient, Unmanned Aerial Vehicle(UAV).

DOI: https://doi.org/10.15623/ijret.2017.0611016