Boundary-layer development and skin friction at Mach number 3.05 / Paul F. Brinich and Nick S. Diaconis.
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1952.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2742. |
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| Abstract: | Boundary-layer studies consisting of schlieren observations and momentum surveys were made on hollow cylinder models with their axes alined (SIC) parallel to the stream. Results were obtained for three model diameters and for natural and artificially induced turbulent boundary layer flows. Transition Reynolds numbers were found to decrease with decreases in leading-edge thickness and with reductions in tunnel pressure level. Turbulent temperature-recovery factors generally decreased with increasing Reynolds number and were a maximum for the smallest transition Reynolds numbers. The results of this investigation appeared to be consistent with the theoretical turbulent friction formulas of Wilson and with the extended Frankl-Voishel analysis of Rubesin, Maydew, and Varga. Velocity profiles in the outer portion of the boundary layer could be approximated reasonably with a 1/7 power profile and were found to be approximately similar in this region. Velcoity profiles given by the Karman universal turbulent boundary-layer profile parameters were found to be similar in the laminar sublayer and in the turbulent region. |
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| Item Description: | "July 1952." NACA TN Number 2742. |
| Physical Description: | 49 pages : illustrations ; 28 cm. |
| Bibliography: | Includes bibliographical references. |
| Action Note: | committed to retain 20230101 20480101 Alliance Shared Trust https://www.coalliance.org/shared-print-archiving-policies. |