GOE 233 (MVA CA4) AIRFOIL (goe233-il)
GOE 233 (MVA CA4) AIRFOIL - Gottingen 233 (MVA CA4) airfoil
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(goe233-il) GOE 233 (MVA CA4) AIRFOIL Gottingen 233 (MVA CA4) airfoil Max thickness 11.6% at 19.8% chord. Max camber 8.2% at 49.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 233 (MVA CA4) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0119300 0.0265600
0.0242000 0.0371200
0.0488500 0.0531600
0.0735700 0.0659900
0.0983400 0.0768300
0.1479900 0.0929000
0.1977600 0.1032800
0.2974700 0.1167400
0.3974100 0.1194000
0.4975300 0.1138700
0.5978200 0.1005400
0.6982200 0.0821200
0.7987300 0.0584900
0.8993200 0.0313700
0.9496400 0.0164600
1.0000000 0.0015500
0.0000000 0.0000000
0.0127600 -.0121200
0.0253200 -.0149500
0.0504200 -.0195100
0.0754500 -.0205700
0.1004600 -.0210300
0.1503900 -.0178400
0.2002700 -.0126600
0.2998500 0.0069900
0.3992800 0.0333400
0.4989100 0.0505000
0.5987700 0.0567600
0.6988300 0.0538300
0.7991200 0.0405000
0.8995600 0.0204800
0.9498000 0.0092600
1.0000000 -.0015500
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Polars for GOE 233 (MVA CA4) AIRFOIL (goe233-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe233-il | 50,000 | 9 | 26.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 50,000 | 5 | 33.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 100,000 | 9 | 60.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 100,000 | 5 | 63.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 200,000 | 9 | 86.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 200,000 | 5 | 87.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 500,000 | 9 | 120.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 500,000 | 5 | 115.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe233-il | 1,000,000 | 9 | 146.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe233-il | 1,000,000 | 5 | 134.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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