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Published November 2, 2015 | Submitted
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An Experimental Investigation of Hypersonic Stagnation Temperature Problems

Abstract

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.

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.

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August 19, 2023
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January 13, 2024