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RANS Simulations of Aerodynamic Performance of NACA 0015 Flapped Airfoil

Mechanical & Aeronautical Engineering Department, Clarkson University, Potsdam, NY 13699, USA
Aerospace Engineering, Mississippi State University, Starkville, MS 39762, USA
Authors to whom correspondence should be addressed.
Academic Editor: Asterios Pantokratoras
Received: 8 August 2016 / Revised: 6 December 2016 / Accepted: 23 December 2016 / Published: 5 January 2017
(This article belongs to the Special Issue Computational Fluid Dynamics)
An analysis of 2D subsonic flow over an NACA 0015 airfoil with a 30% trailing edge flap at a constant Reynolds number of 106 for various incidence angles and a range of flap deflections is presented. The steady-state governing equations of continuity and momentum conservation are solved combined with the realizable k-ε turbulence model using the ANSYS-Fluent code (Version 13.7, ANSYS, Inc., Canonsburg, PA, USA). The primary objective of the study is to provide a comprehensive understanding of flow characteristics around the NACA 0015 airfoil as a function of the angle of attack and flap deflection at Re = 106 using the realizable k-ε turbulence model. The results are validated through comparison of the predictions with the free field experimental measurements. Consistent with the experimental observations, the numerical results show that increased flap deflections increase the maximum lift coefficient, move the zero-lift angle of attack (AoA) to a more negative value, decrease the stall AoA, while the slope of the lift curve remains unchanged and the curve just shifts upwards. In addition, the numerical simulations provide limits for lift increment Δ C l and Cl, max values to be 1.1 and 2.2, respectively, obtained at a flap deflection of 50°. This investigation demonstrates that the realizable k-ε turbulence model is capable of predicting flow features over an airfoil with and without flap deflections with reasonable accuracy. View Full-Text
Keywords: aerodynamics; lift; drag; NACA 0015; flap; k aerodynamics; lift; drag; NACA 0015; flap; k
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MDPI and ACS Style

Obeid, S.; Jha, R.; Ahmadi, G. RANS Simulations of Aerodynamic Performance of NACA 0015 Flapped Airfoil. Fluids 2017, 2, 2.

AMA Style

Obeid S, Jha R, Ahmadi G. RANS Simulations of Aerodynamic Performance of NACA 0015 Flapped Airfoil. Fluids. 2017; 2(1):2.

Chicago/Turabian Style

Obeid, Sohaib, Ratneshwar Jha, and Goodarz Ahmadi. 2017. "RANS Simulations of Aerodynamic Performance of NACA 0015 Flapped Airfoil" Fluids 2, no. 1: 2.

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