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The performance of an aircraft wing mostly depends on the aerodynamic characteristics i.e. lift force, drag force, pressure
distribution, a 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 consists 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 (1000000, 2000000, 3000000, and 4000000) at different angle of attack (0, 3,6, and 9). 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 obtained in Re-4000000 
at angle of attack 9 whereas low drag coefficient obtained in Re-1000000 at AOA 0.

Additional Authors: Husain Mehdi, Shwetanshu Gaurav, Mudit Sharma

Document Type: Research Paper Topic Area: Other Submitted: 13th Jun 2017
Institution: Meerut Institute of Technology, Meerut Department: MECHANICAL Country: India
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