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Impact Pressure and Total Temperature Interpretation at Hypersonic Mach Number


Graves, Jack Carl (1954) Impact Pressure and Total Temperature Interpretation at Hypersonic Mach Number. Engineer's thesis, California Institute of Technology. doi:10.7907/V04Q-TF29.


Results are presented of an experimental investigation of impact-pressure and total-temperature interpretation at a nominal Mach number of 5.6. The data indicate that the Rayleigh equation, which assumes non-viscous flow, requires correction at low free-stream Reynolds numbers. These viscous effects are detected at Reynolds numbers (based on impact-probe diameter) as high as 6000, and they continue to increase with decreasing Reynolds numbers. At the low pressure limit of the facilities used in this investigation, the maximum viscous correction is 2.5 percent for a Reynolds number of 425. The calibration curves for the recovery factor of a total-temperature probe are given, plus an analysis of suitable parameters with which to present this information. For the limited range of total temperatures of 200[degrees]F to 260[degrees]F, and a nominal Mach number of 5.6, single calibration curves are shown using either the free-stream Reynolds number, or the Nusselt number of the flow inside the probe (based on thermocouple wire diameter) as parameters.

Item Type:Thesis (Engineer's thesis)
Subject Keywords:Aeronautical Engineering
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Nagamatsu, Henry T.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1954
Record Number:CaltechETD:etd-12182003-100211
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:5039
Deposited By: Imported from ETD-db
Deposited On:19 Dec 2003
Last Modified:08 Jun 2023 22:06

Thesis Files

PDF (Graves_jc_1954.pdf) - Final Version
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