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Direct Numerical Simulation of Hypersonic Boundary Layer Transition over a Blunt Cone
Direct numerical simulation of transition flow over a blunt cone with a freestream Mach number of 6, Reynolds number of 10,000 based on the nose radius, and a 1-deg angle of attack is performed by using a seventh-order weighted essentially nonoscillatory scheme for the convection terms of the Navier-Stokes equations, together with an eighth-order central finite difference scheme for the viscous terms. The wall blow-and-suction perturbations, including random perturbation and multifrequencydoi:10.2514/1.37305 fatcat:7pb5liifszdvjh6z57zj6jon6m