The calculation of the combustion in a hypersonic boundary layer near the chemical equilibrium
Abstract
The investigation is related to a study conducted by Chung (1965) concerning the cooling of hypersonic flight vehicles by the injection of a combustible gas into the stagnation point boundary layer formed at the body. The investigation takes into account the equilibrium conditions for the basic solution. Deviations from local chemical equilibrium are considered with the aid of higher approximations. Attention is given to the characteristics of the combustion process close to the wall.
- Publication:
-
Zeitschrift Angewandte Mathematik und Physik
- Pub Date:
- March 1975
- Bibcode:
- 1975ZaMP...26..211P
- Keywords:
-
- Chemical Equilibrium;
- Gas Injection;
- Hypersonic Boundary Layer;
- Hypersonic Combustion;
- Stagnation Point;
- Approximation;
- Asymptotic Methods;
- Boundary Layer Flow;
- Equilibrium Flow;
- Wall Flow;
- Fluid Mechanics and Heat Transfer