Iterative solution of the equations for steady viscous compressible flow, based on similitude
Abstract
A study was made of an iterative procedure for solving numerically the equations of steady viscous compressible flow. The method, based on a principle of similitude, was tested for the case of laminar twodimensional hypersonic flow into a compression corner. The first two iterations gave an accurate description of the boundary layer, using less than 1 percent of the computer time required for timemarching integration of the equations for transient twodimensional flow. However, the equations of the third iteration, in which development of separated flow and recirculation was to have begun, proved unstable. A plausible explanation for the unstable behavior of the third iterate was found. On that basis, alternate equations were developed that may permit stable iteration.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 November 1974
 Bibcode:
 1974STIN...7527315T
 Keywords:

 Compressible Flow;
 Hypersonic Flow;
 Iterative Solution;
 Steady Flow;
 Boundary Layer Flow;
 Computer Techniques;
 NavierStokes Equation;
 Fluid Mechanics and Heat Transfer