MEASUREMENT OF HEAT TRANSFER AT NOZZLE THROAT BY IMBEDDED PYROMETER METHOD,
JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
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A newly developed transistorized radiation pyrometer was employed in temperature and heat transfer studies of the nozzle of a rocket exhaust powered Mach 5 hypersonic wind tunnel. The investigation also involved boundary layer measurements and spectroscopic determination of gas species concentration.
- Test Facilities, Equipment and Methods
- Fluid Mechanics