GOE 335 (D.F.W.) AIRFOIL (goe335-il)
GOE 335 (D.F.W.) AIRFOIL - Gottingen 335 (D.F.W.) airfoil
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(goe335-il) GOE 335 (D.F.W.) AIRFOIL Gottingen 335 (D.F.W.) airfoil Max thickness 6.9% at 20% chord. Max camber 4.8% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 335 (D.F.W.) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0160900
0.0250000 0.0251900
0.0500000 0.0383800
0.0750000 0.0480600
0.1000000 0.0567500
0.1500000 0.0686300
0.2000000 0.0765000
0.3000000 0.0812500
0.4000000 0.0790000
0.5000000 0.0737500
0.6000000 0.0640000
0.7000000 0.0507500
0.8000000 0.0355000
0.9000000 0.0202500
0.9500000 0.0106300
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0069100
0.0250000 -.0073100
0.0500000 -.0056300
0.0750000 -.0034400
0.1000000 -.0007500
0.1500000 0.0041200
0.2000000 0.0080000
0.3000000 0.0142500
0.4000000 0.0170000
0.5000000 0.0162500
0.6000000 0.0140000
0.7000000 0.0107500
0.8000000 0.0070000
0.9000000 0.0037500
0.9500000 0.0021300
1.0000000 0.0000000
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Polars for GOE 335 (D.F.W.) AIRFOIL (goe335-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe335-il | 50,000 | 9 | 38.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 50,000 | 5 | 41.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 100,000 | 9 | 56.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 100,000 | 5 | 57.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 200,000 | 9 | 75.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 200,000 | 5 | 75.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 500,000 | 9 | 102.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 500,000 | 5 | 100.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 1,000,000 | 9 | 123.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 1,000,000 | 5 | 119.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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