Accession Number:

AD0631821

Title:

MEASUREMENT OF HEAT TRANSFER AT NOZZLE THROAT BY IMBEDDED PYROMETER METHOD,

Descriptive Note:

Corporate Author:

JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB

Personal Author(s):

Report Date:

1964-01-01

Pagination or Media Count:

18.0

Abstract:

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.

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Fluid Mechanics
  • Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE