Effects of surface roughness and vortex generators on the LS(1)-0417MOD airfoil Metadata
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Title
- Main Title Effects of surface roughness and vortex generators on the LS(1)-0417MOD airfoil
Creator
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Author: Reuss, R. L.Creator Type: Personal
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Author: Hoffman, M. J.Creator Type: Personal
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Author: Gregorek, G. M.Creator Type: PersonalCreator Info: Ohio State Univ., Columbus, OH (United States)
Contributor
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Sponsor: United States. Department of Energy.Contributor Type: OrganizationContributor Info: USDOE, Washington, DC (United States)
Publisher
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Name: National Renewable Energy Laboratory (U.S.)Place of Publication: Golden, ColoradoAdditional Info: National Renewable Energy Lab., Golden, CO (United States)
Date
- Creation: 1995-12-01
Language
- English
Description
- Content Description: An 18-inch constant-chord model of the LS(l)-0417MOD airfoil section was tested under two dimensional steady state conditions ate University 7{times}10 Subsonic Wind Tunnel. The objective was to document section lift and moment characteristics model and air flow conditions. Surface pressure data was acquired at {minus}60{degrees} through + 230{degrees} geometric angles of attack, at a nominal 1 million Reynolds number. Cases with and without leading edge grit roughness were investigated. The leading edge mulated blade conditions in the field. Additionally, surface pressure data were acquired for Reynolds numbers of 1.5 and 2.0 million, with and without leading edge grit roughness; the angle of attack was limited to a {minus}20{degrees} to 40{degrees} range. In general, results showed lift curve slope sensitivities to Reynolds number and roughness. The maximum lift coefficient was reduced as much as 29% by leading edge roughness. Moment coefficient showed little sensitivity to roughness beyond 50{degrees} angle of attack, but the expected decambering effect of a thicker boundary layer with roughness did show at lower angles. Tests were also conducted with vortex generators located at the 30% chord location on the upper surface only, at 1 and 1.5 million Reynolds numbers, with and without leading edge grit roughness. In general, with leading edge grit roughness applied, the vortex generators restored 85 percent of the baseline level of maximum lift coefficient but with a more sudden stall break and at a higher angle of attack than the baseline.
- Physical Description: 116 p.
Subject
- Keyword: Testing
- Keyword: Vortices
- Keyword: Aerodynamics
- Keyword: Wind Tunnels
- Keyword: Roughness
- Keyword: Wind Power
- Keyword: Airfoils
- Keyword: Horizontal Axis Turbines
- Keyword: Experimental Data
- STI Subject Categories: 17 Wind Energy
Source
- Other Information: PBD: Dec 1995
Collection
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Name: Office of Scientific & Technical Information Technical ReportsCode: OSTI
Institution
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Name: UNT Libraries Government Documents DepartmentCode: UNTGD
Resource Type
- Report
Format
- Text
Identifier
- Other: DE96000495
- Report No.: NREL/TP--442-6474
- Grant Number: AC36-83CH10093
- DOI: 10.2172/205202
- Office of Scientific & Technical Information Report Number: 205202
- Archival Resource Key: ark:/67531/metadc672808
Note
- Display Note: OSTI as DE96000495