Abstract
Transonic flow over an airfoil involves shock induced oscillation at certain free steam Mach number and angle of attack due to the interaction of shock wave with airfoil boundary layer which consequences fluctuating lift and drag coefficient, aero acoustic noise and vibration, high cycle fatigue failure (HCF), buffeting and so on. In the present study, Reynolds Averaged Navier-Stokes (RANS) equations have been used to predict the transonic buffer and corresponding aerodynamics behaviour over NASA SC(2) 0714 supercritical airfoil. RANS computations have been performed at free stream Mach number of 0.77 while the angle of attack was varied from 2° to 7°. The results obtained from the numerical computation have been validated with the experimental results. Mach contour, lift and drag coefficient, and pressure history over the airfoil surface have been analyzed and confirmed the transonic buffet phenomena.
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