Abstract
In the present study, numerical investigation of the turbulent flow over a biconvex airfoil at compressible and high Mach numbers flow is done using computational fluid dynamics (CFD). The flow is considered as turbulent, two-dimensional, steady and compressible. For this purpose, three Reynolds number of 2.4 × 107, 2.9 × 107 and 3.3 × 107 are considered. The simulations are implemented using the commercial software Ansys Fluent 16. The results are obtained with Reynolds-averaged Navier–Stokes (RANS), and for simulating the flow turbulence, SST k–ω turbulence model is carried out. The results show that the lift coefficient (CL) and drag coefficient (CD) increase by the increment of the angle of attack (α). The lift-to-drag ratio (CL/CD) is improved by increasing the Mach number (Ma) and cause to delay the boundary layer separation. Increasing the Mach number affects the stall angle which causes to increase it from α = 22° to α = 30° from Ma = 1 to Ma = 1.4.
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