GOE 630 AIRFOIL (goe630-il)
GOE 630 AIRFOIL - Gottingen 630 airfoil
| Details | Dat file | Parser | |
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(goe630-il) GOE 630 AIRFOIL Gottingen 630 airfoil Max thickness 12.6% at 29.8% chord. Max camber 7.7% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 630 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0120600 0.0281900
0.0243600 0.0413800
0.0490300 0.0622600
0.0737900 0.0781400
0.0985800 0.0915300
0.1482700 0.1118000
0.1980500 0.1255700
0.2978700 0.1371200
0.3979000 0.1356700
0.4980400 0.1262200
0.5983000 0.1097700
0.6986500 0.0868300
0.7990600 0.0603900
0.8995100 0.0314400
0.9497500 0.0162200
1.0000000 0.0000000
0.0000000 0.0000000
0.0127000 -.0128000
0.0252300 -.0151100
0.0502100 -.0137200
0.0751800 -.0113300
0.1001300 -.0084500
0.1500400 -.0026700
0.1999500 0.0031000
0.2998200 0.0116500
0.3997300 0.0177000
0.4996900 0.0197500
0.5997100 0.0188000
0.6996800 0.0161100
0.7998101 0.0124000
0.8999100 0.0059500
0.9499700 0.0022200
1.0000000 0.0000000
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Polars for GOE 630 AIRFOIL (goe630-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe630-il | 50,000 | 9 | 7.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 100,000 | 9 | 48.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 100,000 | 5 | 54.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 200,000 | 9 | 74.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 200,000 | 5 | 73.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 500,000 | 9 | 103.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 500,000 | 5 | 99.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 1,000,000 | 9 | 129 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 1,000,000 | 5 | 123.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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