Numerical Solution of the Flow Field about Two-Dimensional Shaved Circular Cylinders in Supersonic Flow.
Scientific interim rept.,
BOSTON UNIV MASS ENGINEERING LABS
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A theoretical investigation of the flow of a perfect gas over two-dimensional shaved circular cylinders has been conducted at supersonic Mach numbers for the purpose of obtaining shock wave shapes. An integral relation method is used for the numerical solution of the flow in the subsonic-transonic region. For the supersonic region, the method of characteristics is used to obtain a numerical solution. The computer programs of both methods are developed for calculating the properties of the flow field. The starting values for the characteristic method are obtained from the integral relation method. Numerical solutions have been 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. Results for the simple circular cylinder are also shown, and compared with the results obtained by other authors.
- Numerical Mathematics
- Fluid Mechanics