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An Experimental Investigation of Hypersonic Stagnation Temperature Problems

Wood, Richard D. (1959) An Experimental Investigation of Hypersonic Stagnation Temperature Problems. Hypersonic Research Project Memorandum, 50. California Institute of Technology , Pasadena, CA. (Unpublished)

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An experimental investigation of single-shielded hypersonic stagnation temperature probes was conducted in the GALCIT Leg No. 1 hypersonic wind tunnel and in the Jet Propulsion Laboratory 12-inch supersonic wind tunnel. By the combined use of both shield and base heating, a probe recovery factor of r = 1.0 was obtained over a range of Reynolds numbers at M_∞ = 5.75. By using the experimental data and simple heat balance equations, the probe losses, for the conditions investigated, were found to be in the proportion: shield conduction loss - 15 base conduction loss - 3 thermocouple conduction loss - 1 thermocouple radiation loss - 3/100 The typical decrease in probe recovery factor observed for decreasing Reynolds number appears to be related to a decrease in the base temperature and not to the wire conduction loss as commonly assumed. An optimum probe vent to entrance area ratio of A_v/A_e ≈ 1/2 was found and is shown to be a function of the number of vent holes used in the shield. No single calibration parameter was found that could relate the experimental recovery factors under all conditions.

Item Type:Report or Paper (Technical Report)
Additional Information:Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 6b0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.
Group:Hypersonic Research Project
Funding AgencyGrant Number
U.S. Army Office of OrdnanceDA-04-495-Ord-19
Series Name:Hypersonic Research Project Memorandum
Issue or Number:50
Record Number:CaltechAUTHORS:20151030-161008298
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:61757
Deposited On:02 Nov 2015 21:19
Last Modified:03 Oct 2019 09:11

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