SG6051 (sg6051-il)
SG6051 - Selig / Giguere SG6051 wind turbine airfoil
| Details | Dat file | Parser | |
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(sg6051-il) SG6051 Selig / Giguere SG6051 wind turbine airfoil Max thickness 12% at 35.7% chord. Max camber 3.1% at 49.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SG6051
1.00000 .00500
.99790 .00527
.99187 .00631
.98234 .00826
.96969 .01097
.95403 .01425
.93543 .01810
.91410 .02256
.89031 .02759
.86430 .03312
.83636 .03906
.80674 .04530
.77574 .05168
.74358 .05795
.71038 .06395
.67633 .06962
.64160 .07477
.60629 .07931
.57064 .08320
.53475 .08631
.49871 .08866
.46275 .09019
.42700 .09088
.39160 .09080
.35675 .08992
.32259 .08828
.28931 .08595
.25709 .08295
.22611 .07934
.19655 .07516
.16857 .07045
.14233 .06527
.11797 .05967
.09560 .05370
.07537 .04745
.05737 .04097
.04167 .03436
.02838 .02770
.01756 .02109
.00931 .01469
.00369 .00848
.00058 .00263
.00042 -.00220
.00365 -.00654
.00985 -.01097
.01874 -.01489
.03064 -.01812
.04567 -.02084
.06366 -.02323
.08447 -.02531
.10794 -.02708
.13392 -.02857
.16222 -.02979
.19263 -.03075
.22493 -.03144
.25883 -.03183
.29407 -.03182
.33051 -.03112
.36831 -.02972
.40753 -.02795
.44777 -.02626
.48846 -.02473
.52924 -.02320
.56988 -.02165
.61011 -.02008
.64967 -.01854
.68829 -.01704
.72569 -.01560
.76161 -.01423
.79579 -.01293
.82796 -.01165
.85800 -.01039
.88576 -.00922
.91097 -.00824
.93337 -.00744
.95273 -.00678
.96889 -.00613
.98190 -.00546
.99169 -.00501
.99787 -.00493
1.00000 -.00500
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Polars for SG6051 (sg6051-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sg6051-il | 50,000 | 9 | 35.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 50,000 | 5 | 34.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 100,000 | 9 | 58.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 100,000 | 5 | 57.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 200,000 | 9 | 82.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 200,000 | 5 | 78.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 500,000 | 9 | 113 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 500,000 | 5 | 102.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 1,000,000 | 9 | 133.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 1,000,000 | 5 | 115.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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