GOE 240 (KOLLER) AIRFOIL (goe240-il)
GOE 240 (KOLLER) AIRFOIL - Gottingen 240 (KOLLER) airfoil
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(goe240-il) GOE 240 (KOLLER) AIRFOIL Gottingen 240 (KOLLER) airfoil Max thickness 7% at 29.9% chord. Max camber 5.2% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 240 (KOLLER) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123600 0.0181900
0.0247900 0.0284900
0.0496900 0.0414700
0.0746000 0.0529600
0.0995500 0.0606500
0.1494700 0.0711200
0.1994100 0.0785000
0.2993600 0.0850500
0.3993600 0.0853000
0.4994000 0.0796500
0.5994700 0.0708000
0.6995800 0.0565500
0.7997000 0.0402000
0.8998300 0.0232500
0.9499100 0.0119200
1.0000000 0.0011000
0.0000000 0.0000000
0.0125600 -.0085100
0.0250600 -.0084100
0.0500500 -.0071200
0.0750300 -.0037400
0.1000000 -.0003500
0.1499700 0.0043200
0.1999300 0.0089000
0.2998900 0.0150500
0.3998700 0.0179000
0.4998700 0.0176500
0.5998800 0.0157000
0.6999100 0.0116500
0.7999500 0.0070000
0.8999800 0.0024500
0.9500000 0.0006200
1.0000000 -.0011000
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Polars for GOE 240 (KOLLER) AIRFOIL (goe240-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe240-il | 50,000 | 9 | 37.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 50,000 | 5 | 43.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 100,000 | 9 | 62.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 100,000 | 5 | 62.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 200,000 | 9 | 83.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 200,000 | 5 | 78.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 500,000 | 9 | 107.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 500,000 | 5 | 91.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 1,000,000 | 9 | 121.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 1,000,000 | 5 | 99.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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