GOE 633 AIRFOIL (goe633-il)
GOE 633 AIRFOIL - Gottingen 633 airfoil
| Details | Dat file | Parser | |
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(goe633-il) GOE 633 AIRFOIL Gottingen 633 airfoil Max thickness 13.8% at 19.7% chord. Max camber 4% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 633 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0117300 0.0248600
0.0238300 0.0377400
0.0482600 0.0560000
0.0728500 0.0692600
0.0975700 0.0785200
0.1471300 0.0925600
0.1968500 0.1016000
0.2966800 0.1072000
0.3967800 0.1038000
0.4971400 0.0924100
0.5976700 0.0750300
0.6983200 0.0541500
0.7989500 0.0337700
0.8994900 0.0163800
0.9497500 0.0079400
1.0000000 0.0000000
0.0000000 0.0000000
0.0131200 -.0200900
0.0257800 -.0252000
0.0509700 -.0314200
0.0761100 -.0356400
0.1011600 -.0373600
0.1511900 -.0383100
0.2011100 -.0357700
0.3009000 -.0291700
0.4007600 -.0245800
0.5006700 -.0214800
0.6006200 -.0198800
0.7006100 -.0197800
0.8005600 -.0181800
0.9003600 -.0115900
0.9501899 -.0060400
1.0000000 0.0000000
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Polars for GOE 633 AIRFOIL (goe633-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe633-il | 50,000 | 9 | 9.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 50,000 | 5 | 26.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 100,000 | 9 | 43.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 100,000 | 5 | 48.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 200,000 | 9 | 67.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 200,000 | 5 | 66.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 500,000 | 9 | 94.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 500,000 | 5 | 90.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe633-il | 1,000,000 | 9 | 118.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe633-il | 1,000,000 | 5 | 102.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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