Impact pressure and total temperature interpretation at hypersonic mach number

• Main Author: Graves, J. C.
• Format: Others
• Published: 1954
• Online Access: https://thesis.library.caltech.edu/5039/1/Graves_jc_1954.pdf; Graves, J. C. (1954) Impact pressure and total temperature interpretation at hypersonic mach number. Engineer's thesis, California Institute of Technology. doi:10.7907/V04Q-TF29. https://resolver.caltech.edu/CaltechETD:etd-12182003-100211 <https://resolver.caltech.edu/CaltechETD:etd-12182003-100211>

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.