Combustion of hydrogen injected into a supersonic airstream (the SHIP computer program)
Abstract
The mathematical and physical basis of the SHIP computer program which embodies a finitedifference, implicit numerical procedure for the computation of hydrogen injected into a supersonic airstream at an angle ranging from normal to parallel to the airstream main flow direction is described. The physical hypotheses built into the program include: a twoequation turbulence model, and a chemical equilibrium model for the hydrogenoxygen reaction. Typical results for equilibrium combustion are presented and exhibit qualitatively plausible behavior. The computer time required for a given case is approximately 1 minute on a CDC 7600 machine. A discussion of the assumption of parabolic flow in the injection region is given which suggests that improvement in calculation in this region could be obtained by use of the partially parabolic procedure of Pratap and Spalding. It is concluded that the technique described herein provides the basis for an efficient and reliable means for predicting the effects of hydrogen injection into supersonic airstreams and of its subsequent combustion.
 Publication:

Final Report Fluid Mechanics and Thermal Systems
 Pub Date:
 April 1977
 Bibcode:
 1977fmts.rept.....M
 Keywords:

 Computer Programs;
 Hydrogen Oxygen Engines;
 Injection;
 Supersonic Combustion;
 Chemical Equilibrium;
 Finite Difference Theory;
 Turbulence Models;
 Fluid Mechanics and Heat Transfer