A nonlinear theory for predicting the effects of unsteady laminar, turbulent, or transitional boundary layers on the attenuation of shock waves in a shock tube with experimental comparison / by Robert L. Trimpi and Nathaniel B. Cohen.
The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the...
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| Main Authors: | , |
|---|---|
| Corporate Author: | |
| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Aeronautics and Space Administration,
1961.
|
| Series: | NASA technical report ;
R-85. |
| Subjects: |
MARC
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| 100 | 1 | |a Trimpi, Robert L., |e author. |0 http://id.loc.gov/authorities/names/no2006133705 |1 http://isni.org/isni/0000000383682790. | |
| 245 | 1 | 2 | |a A nonlinear theory for predicting the effects of unsteady laminar, turbulent, or transitional boundary layers on the attenuation of shock waves in a shock tube with experimental comparison / |c by Robert L. Trimpi and Nathaniel B. Cohen. |
| 264 | 1 | |a Washington, D.C. : |b National Aeronautics and Space Administration, |c 1961. | |
| 300 | |a 56 pages : |b illustrations ; |c 26 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 NASA technical report ; |v R-85. | |
| 504 | |a Includes bibliographical references (page 55) | ||
| 520 | |a The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the theory to large attenuations; and (c) transition effects are considered. Curves are presented for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers. Comparison of theory and experimental data for shock-wave strengths between 1.5 and 10 over a wide range of Reynolds numbers shows good agreement with the nonlinear theory evaluated for a transition Reynolds number of 2.5 x 10⁶ | ||
| 650 | 0 | |a Skin friction (Aerodynamics) |0 http://id.loc.gov/authorities/subjects/sh85123197. | |
| 650 | 0 | |a Shock tubes. |0 http://id.loc.gov/authorities/subjects/sh85121714. | |
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| 650 | 7 | |a Skin friction (Aerodynamics) |2 fast |0 (OCoLC)fst01120142. | |
| 700 | 1 | |a Cohen, Nathaniel B., |e author. |0 http://id.loc.gov/authorities/names/no2007128055. | |
| 710 | 2 | |a Langley Research Center. |0 http://id.loc.gov/authorities/names/n79134855 |1 http://isni.org/isni/0000000406376754. | |
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