GOE 290 (MVA 290) AIRFOIL (goe290-il)
GOE 290 (MVA 290) AIRFOIL - Gottingen 290 (MVA 290) airfoil
| Details | Dat file | Parser | |
|
(goe290-il) GOE 290 (MVA 290) AIRFOIL Gottingen 290 (MVA 290) airfoil Max thickness 17.6% at 29.1% chord. Max camber 3.9% at 39.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 290 (MVA 290) AIRFOIL
17. 17.
0.0000100 0.0000000
0.0105800 0.0281200
0.0223400 0.0390300
0.0460000 0.0585500
0.0699500 0.0738800
0.0941900 0.0850400
0.1429000 0.1038700
0.1921800 0.1143400
0.2914700 0.1247400
0.3916500 0.1220900
0.4925700 0.1086900
0.5937200 0.0918100
0.6950400 0.0725400
0.7965100 0.0509800
0.8980400 0.0287300
0.9489400 0.0155100
1.0000000 0.0030000
0.0000100 0.0000000
0.0140700 -.0228400
0.0270700 -.0302500
0.0526000 -.0380000
0.0779000 -.0422700
0.1031400 -.0458500
0.1534400 -.0502000
0.2036200 -.0528700
0.3034700 -.0506400
0.4030000 -.0438300
0.5025400 -.0370300
0.6020700 -.0302200
0.7016000 -.0234100
0.8011400 -.0166000
0.9006700 -.0097900
0.9504400 -.0063900
1.0000000 -.0030000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 290 (MVA 290) AIRFOIL (goe290-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe290-il | 50,000 | 9 | 6.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 50,000 | 5 | 22.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 100,000 | 9 | 41.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 100,000 | 5 | 46.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 200,000 | 9 | 69 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 200,000 | 5 | 67 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 500,000 | 9 | 96.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 500,000 | 5 | 84 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe290-il | 1,000,000 | 9 | 112.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe290-il | 1,000,000 | 5 | 92.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||