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The performance of an aircraft wing mostly depend on the aerodynamic characteristics
i.e. lift force, drag force, pressure distribution, ratio of lift to drag etc. In this paper the
influence of aerodynamic performance on two dimensional NACA 4412 airfoil is
investigated. The computational method consist of steady state, incompressible, finite
volume method, spalart-allmaras turbulence model. The flow has been studied with the
help of Navier-Stroke and continuity equations. Numerical simulations were performing
at Reynolds number (1x106, 2x106, 3x106, and 4x106) at different angle of attack (00, 30,
60, and 90). The results give the satisfactory measure of confidence of fidelity of the
simulation. Aerodynamic forces are calculated with different Reynolds number and angle
of attack, after analyzing the data it is found that the higher lift coefficient was obtain in
Re-4x106 at angle of attack 90 whereas low drag coefficient was obtain in Re-1x106 at
AOA-00
Document Type: Article Topic Area: Education Submitted: 3rd Nov 2016 Country: India
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