Investigation of laminar boundary layer in compressible fluids using the Crocco method / E.R. Van Driest.
The Crocco method has been used to compute the skin-friction and heat-transfer coefficients for high-speed air flow in the laminar boundary layer on the flat plate, assuming a Prandtl number of 0.75 and constant specific heat, and using the Sutherland viscosity law. The results are different from th...
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| Main Author: | |
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| Corporate Author: | |
| 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) ;
2597. |
| Subjects: |
MARC
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| 100 | 1 | |a Van Driest, E. R. | |
| 245 | 1 | 0 | |a Investigation of laminar boundary layer in compressible fluids using the Crocco method / |c E.R. Van Driest. |
| 260 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c 1952. | ||
| 300 | |a 78 pages : |b illustrations ; |c 28 cm. | ||
| 336 | |a text |b txt |2 rdacontent. | ||
| 337 | |a unmediated |b n |2 rdamedia. | ||
| 338 | |a volume |b nc |2 rdacarrier. | ||
| 490 | 1 | |a National Advisory Committee for Aeronautics. Technical Note ; |v no. 2597. | |
| 500 | |a "January 1952." | ||
| 500 | |a NACA TN Number 2597. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a The Crocco method has been used to compute the skin-friction and heat-transfer coefficients for high-speed air flow in the laminar boundary layer on the flat plate, assuming a Prandtl number of 0.75 and constant specific heat, and using the Sutherland viscosity law. The results are different from those given by Crocco in that they are based on an ambient temperature of -67.6 degrees F and extend the Mach number range considerably above 5 with variable wall-to-free-stream temperature ratio. Variation of shear, velocity, temperature, and Mach number across the layer are shown. The application of the Crocco method of laminar-boundary-layer analysis is discussed in detail. | |
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| 650 | 0 | |a Laminar flow. |0 http://id.loc.gov/authorities/subjects/sh85074205. | |
| 650 | 0 | |a Laminar boundary layer. |0 http://id.loc.gov/authorities/subjects/sh2003006140. | |
| 650 | 0 | |a Air flow. |0 http://id.loc.gov/authorities/subjects/sh85002635. | |
| 650 | 0 | |a Heat |x Transmission. |0 http://id.loc.gov/authorities/subjects/sh85059767. | |
| 650 | 0 | |a Mathematical analysis. |0 http://id.loc.gov/authorities/subjects/sh85082116. | |
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| 650 | 7 | |a Laminar flow. |2 fast |0 (OCoLC)fst00991079. | |
| 650 | 7 | |a Mathematical analysis. |2 fast |0 (OCoLC)fst01012068. | |
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| 830 | 0 | |a Technical note (United States. National Advisory Committee for Aeronautics) ; |v 2597. |0 http://id.loc.gov/authorities/names/no2009017392. | |
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