GOE 416A AIRFOIL (goe416a-il)
GOE 416A AIRFOIL - Gottingen 416A airfoil
| Details | Dat file | Parser | |
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(goe416a-il) GOE 416A AIRFOIL Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord. Max camber 1.3% at 59.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 416A AIRFOIL
17. 17.
0.0000100 0.0000000
0.0113200 0.0155600
0.0232400 0.0231700
0.0474500 0.0336100
0.0718500 0.0414700
0.0963900 0.0474400
0.1457000 0.0565900
0.1953300 0.0614700
0.2949100 0.0668600
0.3950600 0.0648800
0.4954600 0.0597300
0.5961300 0.0508900
0.6969000 0.0407700
0.7978100 0.0287500
0.8988600 0.0150500
0.9493800 0.0081900
1.0000000 0.0013500
0.0000100 0.0000000
0.0131300 -.0081000
0.0260000 -.0130200
0.0516300 -.0212700
0.0771300 -.0278300
0.1025400 -.0331900
0.1531500 -.0413400
0.2035100 -.0460000
0.3038200 -.0500600
0.4035700 -.0467700
0.5027100 -.0355200
0.6018100 -.0236700
0.7011100 -.0145100
0.8006099 -.0079300
0.9002800 -.0036400
0.9501899 -.0024400
1.0000000 -.0013500
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Polars for GOE 416A AIRFOIL (goe416a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe416a-il | 50,000 | 9 | 31.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 50,000 | 5 | 34 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 100,000 | 9 | 46.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 100,000 | 5 | 47.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 200,000 | 9 | 61.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 200,000 | 5 | 57.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 500,000 | 9 | 71 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 500,000 | 5 | 67.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe416a-il | 1,000,000 | 9 | 80.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe416a-il | 1,000,000 | 5 | 75.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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