Author : Somaling Koti 1
Date of Publication :24th May 2017
Abstract: The work reported here to show the effect of biplane configuration on aerodynamic performance of the NACA 0012 symmetric airfoil. The computational analysis was performed with the help of CFD program which were GAMBIT and FLUENT. The flow around the airfoils was incompressible, steady state, two dimensional Nevier-Stokes equations with different turbulence models were used to simulate the flow nature of aerofoils. This analysis have been carried out by varying the gap between the aerofoils such as 25%C, 50%C, 75%C and 100%C at various angle of attack and operating at Reynolds number 3×106. An interference effect occurs in gap between biplane configurations which can be varied with differ in angle of attack and chord length. The 50%C gap between the aerofoils shows the maximum increase in lift co-efficient. It is observed that biplane configuration provides greater maneuverability performance such as loops and rolls. The computational solutions gives information that increase in lift co- efficient at low speed conditions with little penalty in drag co-efficient. Computed results have been validated with existing experimental data.
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