Corrections To Single Shielded Total Temperature Probes In Subsonic Supersonic And Hypersonic Flow
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| Total Pages | : 0 |
| Release | : 1976 |
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Download Corrections to Single-Shielded Total Temperature Probes in Subsonic, Supersonic, and Hypersonic Flow Book in PDF, Epub and Kindle
A new total temperature measurement correction is developed for the single-shielded type of probe. This method is based on a detailed analysis of the coupled heat transfer-viscous flow region existing within the probe. The correction is valid for all flow-field conditions and requires probe calibration data only in the free stream where flow properties are known. Total temperature measurements on the windward ray of a 4-deg sharp cone at Mach 10 in AEDC Hypersonic Tunnel (C) are used in conjunction with corresponding theoretical predictions to substantiate the present analysis. The new approach appears to be a significant improvement over present methods. (Author).
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| Total Pages | : 0 |
| Release | : 1976 |
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| ISBN | : |
Download Corrections to Single-Shielded Total Temperature Probes in Subsonic, Supersonic, and Hypersonic Flow Book in PDF, Epub and Kindle
A new total temperature measurement correction is developed for the single-shielded type of probe. This method is based on a detailed analysis of the coupled heat transfer-viscous flow region existing within the probe. The correction is valid for all flow-field conditions and requires probe calibration data only in the free stream where flow properties are known. Total temperature measurements on the windward ray of a 4-deg sharp cone at Mach 10 in AEDC Hypersonic Tunnel (C) are used in conjunction with corresponding theoretical predictions to substantiate the present analysis. The new approach appears to be a significant improvement over present methods. (Author).
| Author | : M. O. Varner |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1976 |
| Genre | : Probes (Electronic instruments) |
| ISBN | : |
Download Corrections to Single-shielded Total Temperature Probes in Subsonic, Supersonic, and Hypersonic Flow Book in PDF, Epub and Kindle
A new total temperature measurement correction is developed for the single-shielded type of probe. This method is based on a detailed analysis of the coupled heat transfer-viscous flow region existing within the probe. The correction is valid for all flow-field conditions and requires probe calibration data only in the free stream where flow properties are known. Total temperature measurements on the windward ray of a 4-deg sharp cone at Mach 10 in AEDC Hypersonic Tunnel (C) are used in conjunction with corresponding theoretical predictions to substantiate the present analysis. The new approach appears to be a significant improvement over present methods. (Author).
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| Total Pages | : 1102 |
| Release | : 1973 |
| Genre | : Aeronautics |
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Download Scientific and Technical Aerospace Reports Book in PDF, Epub and Kindle
| Author | : |
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| Total Pages | : 904 |
| Release | : 1973 |
| Genre | : Aeronautics |
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Download STAR Book in PDF, Epub and Kindle
| Author | : Cindy W. Albertson |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1993 |
| Genre | : Temperature measurements |
| ISBN | : |
Download Total Temperature Probes for High-temperature Hypersonic Boundary-layer Measurements Book in PDF, Epub and Kindle
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| Total Pages | : 1540 |
| Release | : 1992 |
| Genre | : Science |
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Download Government Reports Announcements & Index Book in PDF, Epub and Kindle
| Author | : |
| Publisher | : |
| Total Pages | : 488 |
| Release | : 1992 |
| Genre | : Hypersonic planes |
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Download AIAA Fourth International Aerospace Planes Conference: 92-5073 - 92-5107 Book in PDF, Epub and Kindle
| Author | : |
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| Total Pages | : 908 |
| Release | : 199? |
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Download Government reports annual index Book in PDF, Epub and Kindle
| Author | : David L. Goldstein |
| Publisher | : |
| Total Pages | : 17 |
| Release | : 1949 |
| Genre | : Probes (Electronic instruments) |
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Download Design and Calibration of a Total-temperature Probe for Use at Supersonic Speeds Book in PDF, Epub and Kindle
The results of a study of the factors involved in the design of total-temperature probes for use at supersonic speeds have been applied to the design of an instrument to be used in wind-tunnel calibrations. Tests of the probe showed that the calibration factor required in the conversion of the measured temperature to the true total temperature was 0.992 pluse or minus 0.002 for a range of Mach numbers between 1.36 and 2.01. The calibration factor was insensitive to angles of inclination relative to the air stream up to 9 degrees at a Mach number of 1.50.
