GOE 373 AIRFOIL (goe373-il)
GOE 373 AIRFOIL - Gottingen 373 airfoil
| Details | Dat file | Parser | |
|
(goe373-il) GOE 373 AIRFOIL Gottingen 373 airfoil Max thickness 6.5% at 29.9% chord. Max camber 5.1% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 373 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123300 0.0166200
0.0247200 0.0277500
0.0495800 0.0420000
0.0744800 0.0522400
0.0994000 0.0599900
0.1493000 0.0704900
0.1992200 0.0779900
0.2991700 0.0829900
0.3991900 0.0809900
0.4992700 0.0734900
0.5993700 0.0634900
0.6995000 0.0500000
0.7996500 0.0350000
0.8998100 0.0190000
0.9499000 0.0100000
1.0000000 0.0000000
0.0000000 0.0000000
0.0126000 -.0098700
0.0250700 -.0067500
0.0500300 -.0030000
0.0749900 0.0007500
0.0999600 0.0040000
0.1499100 0.0090000
0.1998700 0.0135000
0.2998200 0.0180000
0.3998000 0.0205000
0.4998000 0.0200000
0.5998200 0.0185000
0.6998500 0.0155000
0.7999000 0.0105000
0.8999500 0.0055000
0.9499800 0.0025000
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 373 AIRFOIL (goe373-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe373-il | 50,000 | 9 | 35.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe373-il | 50,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe373-il | 100,000 | 9 | 59 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe373-il | 100,000 | 5 | 61.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe373-il | 200,000 | 9 | 80.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe373-il | 200,000 | 5 | 79 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe373-il | 500,000 | 9 | 105.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe373-il | 500,000 | 5 | 94.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe373-il | 1,000,000 | 9 | 105 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe373-il | 1,000,000 | 5 | 93.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||