Experimental investigation at a Mach number of 2.41 of average skin-friction coefficients and velocity profiles for laminar and turbulent boundary layers and an assessment of probe effects / Robert M. O'Donnell.
An experimental investigation was made of laminar and turbulent boundary layers on the outer surface of a hollow cylinder at a Mach number of 2.41 and over a Reynolds number range of 60,00 to 950,000 per inch. Boundary-layer surveys were made by means of a total-pressure probe for stations ranging f...
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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,
1954.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
3122. |
| Subjects: |
MARC
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| 100 | 1 | |a O'Donnell, Robert M. | |
| 245 | 1 | 0 | |a Experimental investigation at a Mach number of 2.41 of average skin-friction coefficients and velocity profiles for laminar and turbulent boundary layers and an assessment of probe effects / |c Robert M. O'Donnell. |
| 260 | |a Washington, D.C. : |b National Advisory Committee for Aeronautics, |c 1954. | ||
| 300 | |a 38 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 ; |v no. 3122. | |
| 500 | |a "January 1954." | ||
| 500 | |a NACA TN Number 3122. | ||
| 504 | |a Includes bibliographical references. | ||
| 520 | 3 | |a An experimental investigation was made of laminar and turbulent boundary layers on the outer surface of a hollow cylinder at a Mach number of 2.41 and over a Reynolds number range of 60,00 to 950,000 per inch. Boundary-layer surveys were made by means of a total-pressure probe for stations ranging from 0.58 to 8.08 inches from the leading edge. | |
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| 650 | 0 | |a Laminar boundary layer. |0 http://id.loc.gov/authorities/subjects/sh2003006140. | |
| 650 | 0 | |a Turbulent boundary layer. |0 http://id.loc.gov/authorities/subjects/sh85138754. | |
| 650 | 0 | |a Skin friction (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh85123197. | |
| 650 | 0 | |a Aerodynamics, Supersonic. |0 http://id.loc.gov/authorities/subjects/sh85001297. | |
| 650 | 7 | |a Aerodynamics, Supersonic. |2 fast |0 (OCoLC)fst00798221. | |
| 650 | 7 | |a Laminar boundary layer. |2 fast |0 (OCoLC)fst00991078. | |
| 650 | 7 | |a Skin friction (Aerodynamics) |2 fast |0 (OCoLC)fst01120142. | |
| 650 | 7 | |a Turbulent boundary layer. |2 fast |0 (OCoLC)fst01159225. | |
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| 830 | 0 | |a Technical note (United States. National Advisory Committee for Aeronautics) ; |v 3122. |0 http://id.loc.gov/authorities/names/no2009017392. | |
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