GOE 476 AIRFOIL (goe476-il)
GOE 476 AIRFOIL - Gottingen 476 airfoil
| Details | Dat file | Parser | |
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(goe476-il) GOE 476 AIRFOIL Gottingen 476 airfoil Max thickness 14.5% at 29.5% chord. Max camber 5.2% at 39.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 476 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0113900 0.0284400
0.0233900 0.0414100
0.0477200 0.0583600
0.0722000 0.0718200
0.0967900 0.0822700
0.1461900 0.0977000
0.1957800 0.1081400
0.2952600 0.1215200
0.3952300 0.1224100
0.4955400 0.1143300
0.5961700 0.0982500
0.6969500 0.0781800
0.7978700 0.0546200
0.8988700 0.0290600
0.9494100 0.0150300
1.0000000 0.0000000
0.0000000 0.0000000
0.0133800 -.0224800
0.0261700 -.0299800
0.0513800 -.0355000
0.0764400 -.0370200
0.1014500 -.0370400
0.1513100 -.0336000
0.2011600 -.0296500
0.3008900 -.0227700
0.4007000 -.0178700
0.5005300 -.0134800
0.6004300 -.0110800
0.7003601 -.0091900
0.8003399 -.0087900
0.9002301 -.0058900
0.9501300 -.0034400
1.0000000 0.0000000
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Polars for GOE 476 AIRFOIL (goe476-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe476-il | 50,000 | 9 | 6.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe476-il | 50,000 | 5 | 18.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe476-il | 100,000 | 9 | 44.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe476-il | 100,000 | 5 | 49.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe476-il | 200,000 | 9 | 75.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe476-il | 200,000 | 5 | 74.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe476-il | 500,000 | 9 | 108.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe476-il | 500,000 | 5 | 101.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe476-il | 1,000,000 | 9 | 132.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe476-il | 1,000,000 | 5 | 116.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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