Method for calculation of compressible laminar boundary layer with axial pressure gradient and heat transfer / Paul A. Libby and Morris Morduchow.
A rapid and sufficiently accurate method, for most practical purposes, of determining laminar-boundary-layer characteristics in flow with a given free-stream Mach number and given velocity distribution at the edge of the boundary layer is presented. The method can be easily applied to flow with zero...
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| Corporate Author: | |
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1954.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
3157. |
| Subjects: |
MARC
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| 100 | 1 | |a Libby, Paul A. |0 http://id.loc.gov/authorities/names/n80073571 |1 http://isni.org/isni/0000000109520991. | |
| 245 | 1 | 0 | |a Method for calculation of compressible laminar boundary layer with axial pressure gradient and heat transfer / |c Paul A. Libby and Morris Morduchow. |
| 260 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c 1954. | ||
| 300 | |a 44 pages : |b illustrations ; |c 27 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 3157. | |
| 500 | |a "January 1954" | ||
| 500 | |a NACA TN Number 3157. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a A rapid and sufficiently accurate method, for most practical purposes, of determining laminar-boundary-layer characteristics in flow with a given free-stream Mach number and given velocity distribution at the edge of the boundary layer is presented. The method can be easily applied to flow with zero pressure gradient for any (constant) Prandtl number of the number unity and any given temperature distribution along the wall. Numerical examples are given to illustrate the method and the satisfactory accuracy obtained. For flow in an axial pressure gradient, the method can be applied for a Prandtl number of unity and any given uniform wall temperature. The methods developed here are based on an application of the Karman integral method to both the momentum and energy equations, in conjunction with a sixth-degree velocity profile and a seventh-degree stagnation-enthalpy profile. A single boundary-layer thickness and one of the coefficients in the thermal profile are the parameters in this two-parameter method. | |
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| 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 Axial flow |x Pressure. | |
| 650 | 0 | |a Mathematical analysis. |0 http://id.loc.gov/authorities/subjects/sh85082116. | |
| 650 | 0 | |a Integral equations. |0 http://id.loc.gov/authorities/subjects/sh85067088. | |
| 700 | 1 | |a Morduchow, Morris. | |
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| 830 | 0 | |a Technical note (United States. National Advisory Committee for Aeronautics) ; |v 3157. |0 http://id.loc.gov/authorities/names/no2009017392. | |
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