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determination of ram-jet combustion-chamber temperatures by means of total-pressure surveysA method is described by which the total temperature of the gases at the combustion-chamber outlet of a ram-jet engine may be determined from the loss in total pressure measured across the combustion chamber. A working chart is presented by means of which the ratio of the total temperature of the gases at the combustion-chamber outlet to the total temperature of the gases at the combustion-chamber inlet may be determined from the measured loss of total pressure across the combustion chamber and the known values of air flow, total pressure, and total temperature at the combustion-chamber inlet. Values of total-temperature ratio across the combustion chamber of a 20-inch ram jet were obtained in the Cleveland altitude wind tunnel over a range of pressure altitudes from 6000 to 15,000 feet. The difference between the temperature ratio across the combustion chamber determined from the chart and that obtained from the thermocouple measurement was within 6.2 percent of the thermocouple-temperature ratio and was within the accuracy of the thermocouple measurements.
Document ID
19930093753
Document Type
Other
Authors
Pinkel, I Irving
Date Acquired
August 16, 2013
Publication Date
March 3, 1947
Report/Patent Number
NACA-RM-E7C03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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