Numerical integration of the unsteadyflow equations for a twodimensional supersonic free jet
Abstract
The temporal evolution of a free supersonic jet in undisturbed air is characterized numerically from the emergence of the flow from the nozzle until the jet is fully formed, for both inviscid and viscous flow. The Euler and NavierStokes equations are transformed using a timeinvariant coordinate space and integrated by the lambda scheme of Moretti (1979). Shockwave behavior is determined by the shockfitting approach. The computer program is outlined; input parameters are the initial contour of the shock wave, the flow conditions in the nozzle, the pressure and entropy of the surroundings, the Reynolds and Prandtl numbers, and the wall temperature (for viscous flow). The results of two sample calculations are presented and discussed.
 Publication:

Forschung im Ingenieurwesen
 Pub Date:
 1983
 Bibcode:
 1983F&I....49...85W
 Keywords:

 Computational Fluid Dynamics;
 Flow Equations;
 Free Jets;
 Numerical Integration;
 Supersonic Jet Flow;
 Unsteady Flow;
 Euler Equations Of Motion;
 Inviscid Flow;
 NavierStokes Equation;
 Nozzle Flow;
 Two Dimensional Flow;
 Viscous Flow;
 Fluid Mechanics and Heat Transfer