Design and Calibration of Stagnation Temperature Probes for Use at High Supersonic Speeds and Elevated Temperatures
- 1 February 1954
- journal article
- research article
- Published by AIP Publishing in Journal of Applied Physics
- Vol. 25 (2), 231-232
- https://doi.org/10.1063/1.1721609
Abstract
A stagnation temperature probe with a single platinum‐coated silica shield was built for use at high supersonic speeds and elevated temperatures. For large Reynolds numbers the temperature recovery factor of the probe reaches 0.998. It decreases with decreasing Reynolds number and increasing temperature. At temperatures up to 700° K the major thermometric losses of the probe are conduction losses. One single calibration curve is obtained for any one probe by relating the calibration data to the flow conditions inside the probe.Keywords
This publication has 2 references indexed in Scilit:
- An Experimental Study of a Hypersonic Wind-Tunnel DiffuserJournal of the Aeronautical Sciences, 1953
- Summary of Recent Experimental Investigations in the N.O.L. Hyperballistics Wind TunnelJournal of the Aeronautical Sciences, 1951