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Heat transfer and skin friction by an integral method in the compressible laminar boundary layer with a streamwise pressure gradient
- Author / Creator
- Available as
- Online
- Summary
-
A simplified method has been developed for the calculation of heat transfer and skin friction in the compressible laminar boundary layer with an arbitrary Prandtl number near unity and an arbitrary...
A simplified method has been developed for the calculation of heat transfer and skin friction in the compressible laminar boundary layer with an arbitrary Prandtl number near unity and an arbitrary streamwise pressure gradient and wall temperature distribution. By comparison of numerical results with some exact solutions, the method is shown to give accurate results with some exact solutions, the method is shown to give accurate results for the case of boundary-layer cooling when a certain fifth-dgree polynomial is used for the thermal profile. The use of this polynomial also results in recovery factors which are accurate to within a few percent on both the flat plate and the circular cylinder normal to flow.
Details
- Creator
- by Ivan E. Beckwith
- Format
- Books
- Language
- English
- Contributors
- Publication
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- Washington, D.C. : National Advisory Committee for Aeronautics, 1953
- Physical Details
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- 1 online resource (55 pages) : illustrations, tables
- data file
- OCLC
- on1372498087
- Title from title screen (viewed March 6, 2023)
- Date of issue: September 1953.
- Report no. NACA-TN-3005.
- "Langley Aeronautical Laboratory."
- Includes bibliographical references (pages 45-47)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.