Numerical solution of the flow field about two-dimensional shaved circular cylinders in supersonic flow

A theoretical investigation of the flow of a perfect gas over two-dimensional shaved circular cylinders was conducted at supersonic Mach numbers for the purpose of obtaining shock wave shapes. An integral relation method was used for the numerical solution for the flow in the subsonic-transonic region. For the supersonic region, the method of characteristics was used to obtain a numerical solution. The computer programs of both methods were developed for calculating the properties of the flow field. The starting values for the characteristic method were obtained from the integral relation method. Numerical solutions were obtained for a perfect gas in thermodynamic equilibrium with ratio of specific heat, gamma = 1.4 over a Mach number range from 2 to 10. Results for the shock wave shape and stand-off distance are presented for all numerical solutions and comparison is made with experimental results.