SG6042 (sg6042-il)
SG6042 - Selig / Giguere SG6042 wind turbine airfoil (high L/D)
| Details | Dat file | Parser | |
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(sg6042-il) SG6042 Selig / Giguere SG6042 wind turbine airfoil (high L/D) Max thickness 10% at 33.5% chord. Max camber 3.3% at 51.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SG6042
1.00000 .00000
.99806 .00048
.99249 .00203
.98372 .00463
.97210 .00811
.95784 .01223
.94102 .01672
.92161 .02148
.89968 .02657
.87546 .03195
.84915 .03756
.82098 .04333
.79117 .04914
.75995 .05489
.72757 .06038
.69410 .06544
.65962 .07006
.62435 .07417
.58844 .07772
.55208 .08071
.51546 .08310
.47877 .08486
.44221 .08600
.40597 .08648
.37024 .08634
.33522 .08556
.30110 .08415
.26808 .08215
.23633 .07956
.20603 .07639
.17735 .07269
.15044 .06847
.12544 .06379
.10249 .05866
.08169 .05313
.06316 .04726
.04698 .04105
.03315 .03458
.02179 .02795
.01284 .02119
.00619 .01446
.00197 .00797
.00011 .00182
.00035 -.00341
.00371 -.00730
.01068 -.01042
.02068 -.01311
.03369 -.01516
.04982 -.01659
.06901 -.01751
.09117 -.01805
.11611 -.01826
.14365 -.01821
.17358 -.01792
.20570 -.01744
.23979 -.01679
.27559 -.01599
.31286 -.01506
.35135 -.01401
.39078 -.01286
.43089 -.01159
.47140 -.01016
.51208 -.00853
.55277 -.00671
.59330 -.00475
.63345 -.00273
.67298 -.00077
.71161 .00102
.74904 .00255
.78494 .00377
.81900 .00462
.85093 .00510
.88041 .00521
.90718 .00496
.93097 .00442
.95153 .00364
.96868 .00273
.98224 .00178
.99204 .00090
.99800 .00026
1.00000 .00000
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Polars for SG6042 (sg6042-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sg6042-il | 50,000 | 9 | 40 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 50,000 | 5 | 39.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 100,000 | 9 | 62.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 100,000 | 5 | 60.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 200,000 | 9 | 89 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 200,000 | 5 | 82.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 500,000 | 9 | 123.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 500,000 | 5 | 106.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 1,000,000 | 9 | 145.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 1,000,000 | 5 | 110.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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