Influence of rotation of the body and exterior vorticity on the heat transfer near the stagnation point of a blunt body in a supersonic stream

1984 ◽  
Vol 19 (3) ◽  
pp. 499-502 ◽  
Author(s):  
A. A. Markov
Keyword(s):  
Heat Transfer ◽  
Stagnation Point ◽  
Blunt Body ◽  
The Body ◽  
Supersonic Stream

HEAT TRANSFER TO THE STAGNATION POINT OF THE BLUNT BODY IN HYPERSONIC FLOW

1970 ◽  
Author(s):  
L. M. Biberman ◽  
S. Ya. Bronin ◽  
A.N. Lagar'kov
Keyword(s):  
Heat Transfer ◽  
Hypersonic Flow ◽  
Stagnation Point ◽  
Blunt Body

Effect of radiation on heat transfer at the stagnation point of a blunt body

1972 ◽  
Vol 4 (2) ◽  
pp. 48-52 ◽  
Author(s):  
V. P. Stulov ◽  
E. G. Shapiro
Keyword(s):  
Heat Transfer ◽  
Stagnation Point ◽  
Blunt Body

Influence of gaseous heat-shield destruction products on the heat transfer in the neighborhood of the stagnation point on a blunt body

1978 ◽  
Vol 13 (3) ◽  
pp. 440-447 ◽  
Author(s):  
L. M. Biberman ◽  
S. Ya. Bronin ◽  
M. V. Brykin ◽  
A. Kh. Mnatsakanyan
Keyword(s):  
Heat Transfer ◽  
Stagnation Point ◽  
Blunt Body ◽  
Heat Shield

Stagnation Point Heat Transfer Measurements at Super Satellite Speeds

1962 ◽  
Vol 66 (613) ◽  
pp. 53-53 ◽  
Author(s):  
E. Offenhartz ◽  
H. Weisblatt ◽  
R. F. Flagg
Keyword(s):  
Heat Transfer ◽  
Experimental Data ◽  
Heat Conduction ◽  
Shock Tube ◽  
Stagnation Point ◽  
Blunt Body ◽  
Foot Length ◽  
Electronic Heat ◽  
Series Of Experiments ◽  
Stagnation Enthalpy

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.

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