Summary of experimental heat-transfer measurements in turbulent flow for a Mach number range from 0.87 to 5.05 / Maurice J. Brevoort and Barbara D. Arabian.
Heat-transfer measurements have been made in turbulent flow at Mach numbers varying from 0.87 to 5.05 and Reynolds numbers in the range from 1,000,000 to 950,000,000 through the use of an axially symmetric annular nozzle which consists of an inner shaped center body and an outer cylindrical sleeve....
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington :
National Advisory Committee for Aeronautics,
[1958]
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
4248. |
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| Summary: | Heat-transfer measurements have been made in turbulent flow at Mach numbers varying from 0.87 to 5.05 and Reynolds numbers in the range from 1,000,000 to 950,000,000 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. These results are presented in the form of Stanton number and recovery factor as a function of Reynolds number. The Reynolds number is computed for wall and free-stream conditions; that is, the viscosity is taken at either the wall or the free-stream temperature. The results show that the Stanton number decreases with an increase in Reynolds number and usually decreases with an increase in Mach number. The recovery factor appears from these tests to be independent of Mach number and may be represented by a single curve for all Mach numbers in the range of the tests. |
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| Item Description: | "May 1958." NACA TN Number 4248. |
| Physical Description: | 43 pages : illustrations, tables ; 27 cm. |
| Bibliography: | Includes bibliographical references. |