Turbulent-heat-transfer measurements at a Mach number of 3.90 / Maurice J. Brevoort.
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,
1956.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
3734. |
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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 3.90 and for a Reynolds number range of 630,000 to 70,000,000. The heat-transfer-coefficient results are slightly higher than theoretical results for a Mach number of 4.0 and for a ratio of inside-surface temperature to free stream temperture of 4.2. The temperature-recovery factors range from approximately 0.89 at a Reynolds number of 630,000 to approximately 0.86 at a Reynolds number of 70,000,000. |
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| Item Description: | "July 1956." NACA TN Number 3734. |
| Physical Description: | 15 pages : illustrations ; 27 cm. |
| Bibliography: | Includes bibliographical references. |