Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade
Detailed measurements, with a two-component laser-Doppler velocimeter and a thermal anemometer were made near the suction surface leading edge of controlled-diffusion airfoils in cascade. The Reynolds number was near 700,000, Mach number equal to 0.25, and freestream turbulence was at 1.5% ahead of...
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| Format: | Article |
| Language: | English |
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Wiley
1999-01-01
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| Series: | International Journal of Rotating Machinery |
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| Online Access: | http://dx.doi.org/10.1155/S1023621X99000081 |
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| _version_ | 1850224419316695040 |
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| author | Garth V. Hobson Bryce E. Wakefield William B. Roberts |
| author_facet | Garth V. Hobson Bryce E. Wakefield William B. Roberts |
| author_sort | Garth V. Hobson |
| collection | DOAJ |
| description | Detailed measurements, with a two-component laser-Doppler velocimeter and a thermal anemometer were made near the suction surface leading edge of controlled-diffusion airfoils in cascade. The Reynolds number was near 700,000, Mach number equal to 0.25, and freestream turbulence was at 1.5% ahead of the cascade. |
| format | Article |
| id | doaj-art-4f1b6ce97e754719a7000dfcc00c3aeb |
| institution | OA Journals |
| issn | 1023-621X |
| language | English |
| publishDate | 1999-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Rotating Machinery |
| spelling | doaj-art-4f1b6ce97e754719a7000dfcc00c3aeb2025-08-20T02:05:38ZengWileyInternational Journal of Rotating Machinery1023-621X1999-01-0152899810.1155/S1023621X99000081Turbulence Amplification with Incidence at the Leading Edge of a Compressor CascadeGarth V. Hobson0Bryce E. Wakefield1William B. Roberts2Code AA/Hg, Department of Aeronautics and Astronautics, Naval Postgraduate School, 699 Dyer Rd, Rm 137, Monterey, CA 93943-5106, USACode AA/Hg, Department of Aeronautics and Astronautics, Naval Postgraduate School, 699 Dyer Rd, Rm 137, Monterey, CA 93943-5106, USAFlow Application Research Fremont, California, USADetailed measurements, with a two-component laser-Doppler velocimeter and a thermal anemometer were made near the suction surface leading edge of controlled-diffusion airfoils in cascade. The Reynolds number was near 700,000, Mach number equal to 0.25, and freestream turbulence was at 1.5% ahead of the cascade.http://dx.doi.org/10.1155/S1023621X99000081CompressorsBoundary layersSeparation bubblesLaser-Doppler velocimetry. |
| spellingShingle | Garth V. Hobson Bryce E. Wakefield William B. Roberts Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade International Journal of Rotating Machinery Compressors Boundary layers Separation bubbles Laser-Doppler velocimetry. |
| title | Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade |
| title_full | Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade |
| title_fullStr | Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade |
| title_full_unstemmed | Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade |
| title_short | Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade |
| title_sort | turbulence amplification with incidence at the leading edge of a compressor cascade |
| topic | Compressors Boundary layers Separation bubbles Laser-Doppler velocimetry. |
| url | http://dx.doi.org/10.1155/S1023621X99000081 |
| work_keys_str_mv | AT garthvhobson turbulenceamplificationwithincidenceattheleadingedgeofacompressorcascade AT bryceewakefield turbulenceamplificationwithincidenceattheleadingedgeofacompressorcascade AT williambroberts turbulenceamplificationwithincidenceattheleadingedgeofacompressorcascade |