GOE 244 (MVA PR.4) AIRFOIL (goe244-il)
GOE 244 (MVA PR.4) AIRFOIL - Gottingen 244 (MVA PR.4) airfoil
| Details | Dat file | Parser | |
|
(goe244-il) GOE 244 (MVA PR.4) AIRFOIL Gottingen 244 (MVA PR.4) airfoil Max thickness 17.7% at 19.6% chord. Max camber 10% at 49.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 244 (MVA PR.4) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0116000 0.0407600
0.0236000 0.0635200
0.0479600 0.0928600
0.0725200 0.1126000
0.0972100 0.1270400
0.1467400 0.1482300
0.1964000 0.1635200
0.2961400 0.1755200
0.3961800 0.1737200
0.4963800 0.1644200
0.5967900 0.1461300
0.6973600 0.1201400
0.7981000 0.0865600
0.8989900 0.0459800
0.9494900 0.0230900
1.0000000 0.0010000
0.0000000 0.0000000
0.0128700 -.0169200
0.0254300 -.0194400
0.0504800 -.0218900
0.0754700 -.0213400
0.1004600 -.0207900
0.1504100 -.0187900
0.2002800 -.0127900
0.2999400 0.0026000
0.3995900 0.0185900
0.4992100 0.0357800
0.5989500 0.0476800
0.6988500 0.0523700
0.7989600 0.0470800
0.8993800 0.0282900
0.9496900 0.0138900
1.0000000 -.0010000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 244 (MVA PR.4) AIRFOIL (goe244-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe244-il | 50,000 | 9 | 7.9 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 50,000 | 5 | 25 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 100,000 | 9 | 50.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 100,000 | 5 | 47.8 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 200,000 | 9 | 73.3 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 200,000 | 5 | 64.3 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 500,000 | 9 | 92.3 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 500,000 | 5 | 79.5 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe244-il | 1,000,000 | 9 | 105.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe244-il | 1,000,000 | 5 | 98.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||