Turbulent-heat-transfer measurements at a Mach number of 0.87 / Maurice J. Brevoort and Bernard Rashis.
Turbulent-heat-transfer measurements were obtained through the use of an axially symmetric annular nozzle which consists of an inner shaped center body and an outer cylindrical sleeve. Measurements taken along the outer sleeve gave essentially flat-plate results that are free from wall interference...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1955.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
3599. |
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| Summary: | Turbulent-heat-transfer measurements were obtained through the use of an axially symmetric annular nozzle which consists of an inner shaped center body and an outer cylindrical sleeve. Measurements taken along the outer sleeve gave essentially flat-plate results that are free from wall interference and corner effects for a Mach number of 0.87 and for a Reynolds number range from 9,880,000 to 209,000,000. The heat-transfer coeffients are slightly higher than theoretical results for a Mach number of 1.0 and a ratio of inner surface temperature to free-stream temperature of 1.0, and they agree with theoretical results for incompressible flow. The temperature-recovery factors range from 0.899 at a Reynolds number of 9,880,000 to 0.876 at Reynolds number of 209,000,000. |
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| Item Description: | "December 1955." NACA TN Number 3599. |
| Physical Description: | 13 pages : illustrations ; 27 cm. |
| Bibliography: | Includes bibliographical references. |