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Stagnation Point Heat Transfer Measurements at Super Satellite Speeds

Published online by Cambridge University Press:  04 July 2016

E. Offenhartz ,
H. Weisblatt  and
R. F. Flagg
E. Offenhartz
Affiliation:
AVCO Corporation, RAD Division, Wilmington, Massachusetts
H. Weisblatt
Affiliation:
AVCO Corporation, RAD Division, Wilmington, Massachusetts
R. F. Flagg
Affiliation:
AVCO Corporation, RAD Division, Wilmington, Massachusetts
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Extract

Recent lunar and planetary return vehicle studies have stimulated interest concerning the effect upon stagnation point heating due to electronic heat conduction associated with re-entry at speeds greater than 30,000 ft./sec. In order to provide experimental data for comparison with theory, a series of experiments was undertaken in which shock tube techniques were utilised for the measurement of the stagnation point heating of a blunt body over a stagnation enthalpy (Hst/RT0) range of 650 to 900, corresponding to velocities between 32,000 ft./sec. and 39,000 ft. /sec. respectively. The tests were performed in a 1·5 inch diameter shock tube with 3 foot length driver and 16 foot length driven section.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 66 , Issue 613 , January 1962 , pp. 53
Copyright
Copyright © Royal Aeronautical Society 1962

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References

1.Rose, P. (1958). Development of the Calorimeter Heat Transfer Gauge for Use in Shock Tubes. Review of Scientific Instruments, July 1958.CrossRefGoogle Scholar
2.Offenhartz, E. and Weisblatt, H. (1958). Determina tion of the Time History of the Flow Field About Various Blunt Body Shapes and Sizes During Experiments in 1-5 in. Diameter Shock Tube. AVCO-RAD-TR-58-10, July 1958.Google Scholar
3.Adams, M. C. (1960). A Look at the Heat Transfer Problem at Super Satellite Speeds. ARS Paper 1556-60, 1960.Google Scholar
4.Van tassell, W. and Pallone, A. (1961). Similar Solu tions of the Compressible Laminar Boundary Layer Equations for Air in Equilibrium Dissociation and Ioniza- tion With and Without Air Injection in the Stagnation Region. AVCO-RAD-TM-61-22, June 1961.Google Scholar