A shock capturing method for calculating supersonic flow fields
Abstract
A finite difference representation of equations that govern the steady supersonic three dimensional flow of an inviscid ideal gas with constant specific heats is described. A method of using the finite difference equations to calculate solutions of mixed initial and boundary value problems associated with supersonic flow fields is explained. The finite difference equations are arranged so that shock waves that occur in a flow field are computed automatically. Across computed shock waves, the dependent variables change rapidly but the changes cannot be regarded as discontinuous. Numerical results for a symmetric delta wing at zero incidence in a uniform mainstream flow are presented. These results are compared with results from a numerical characteristic method.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 1974
 Bibcode:
 1974STIN...7510381W
 Keywords:

 Delta Wings;
 Finite Difference Theory;
 Supersonic Flow;
 Three Dimensional Flow;
 Boundary Value Problems;
 Computation;
 Difference Equations;
 Flow Distribution;
 Ideal Gas;
 Numerical Analysis;
 Shock Waves;
 Fluid Mechanics and Heat Transfer