Effects of surface roughness and vortex generators on the LS(1)-0417MOD airfoil

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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 ... continued below

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116 p.

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Reuss, R.L.; Hoffman, M.J. & Gregorek, G.M. December 1, 1995.

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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.

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116 p.

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OSTI as DE96000495

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  • Other Information: PBD: Dec 1995

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  • Other: DE96000495
  • Report No.: NREL/TP--442-6474
  • Grant Number: AC36-83CH10093
  • DOI: 10.2172/205202 | External Link
  • Office of Scientific & Technical Information Report Number: 205202
  • Archival Resource Key: ark:/67531/metadc672808

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  • December 1, 1995

Added to The UNT Digital Library

  • June 29, 2015, 9:42 p.m.

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  • March 28, 2016, 1:33 p.m.

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Reuss, R.L.; Hoffman, M.J. & Gregorek, G.M. Effects of surface roughness and vortex generators on the LS(1)-0417MOD airfoil, report, December 1, 1995; Golden, Colorado. (digital.library.unt.edu/ark:/67531/metadc672808/: accessed December 17, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.