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:
-
Soviet Aeronautics
- Pub Date:
- 1975
- Bibcode:
- 1975SvAer..18...43F