Heat and mass transfer during high-enthalpy gas flow in aircraft and rocket engine flow passages
Abstract
The rate of burnup of the heat-protective coating of an aircraft engine's air-gas flow area is studied analytically. A solution is obtained by integrating boundary layer equations in which unsteady-state effects caused by chemical erosion of the flow-area surface are taken into account.
- Publication:
-
Aviatsionnaia Tekhnika
- Pub Date:
- 1975
- Bibcode:
- 1975AvTek..18...54F
- Keywords:
-
- Ablation;
- Aircraft Engines;
- Combustion Chambers;
- High Temperature Gases;
- Rocket Linings;
- Thermal Control Coatings;
- Air Flow;
- Boundary Layer Equations;
- Burnthrough (Failure);
- Enthalpy;
- Flow Geometry;
- Heat Transfer;
- Mass Transfer;
- Protective Coatings;
- Thermal Protection;
- Fluid Mechanics and Heat Transfer