An Explicit Finite-Difference Solution of Hypersonic Flows Using Rational Runge-Kutta Scheme
An explicit method of lines approach has been applied for solving hypersonic flows governed by the Euler, Navier-Stokes and Boltzmann equations. The method is based on a finite difference approximation to spatial derivatives and subsequent time integration using the rational Runge-Kutta scheme. Numerical results are presented for the hypersonic flow over a double ellipse which is a test case of the Workshop on Hypersonic Flows for Reentry Problems, January 22–25, 1990 in Antibes(France).
KeywordsMach Number Pressure Coefficient Hypersonic Flow Finite Difference Approximation STANTON Number
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