Experiments and Analysis Related to External Burning for Propulsion
Interim rept. Feb 1975-Jan 1976
GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
Pagination or Media Count:
The results of first years efforts on an experimental base flow program are reported. The design and checkout for a Mach 3.0 axisymmetric wind tunnel with a model base diameter of 2.25 inches is described, as well as the automated data acquisition system. Experiments are reported on detailed static pressures for the diffuser wall, model wall and base and near wake. Temperature measurements are presented to establish a near adiabatic wall condition. The relationship between the experimental program and propulsive external burning is discussed.
- Test Facilities, Equipment and Methods
- Guided Missiles
- Air Breathing Engines (Unconventional)