GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
GOE 235 (SCHTTE-LANZ) AIRFOIL - Gottingen 235 (SCHATTE-LANZ) airfoil
| Details | Dat file | Parser | |
|
(goe235-il) GOE 235 (SCHTTE-LANZ) AIRFOIL Gottingen 235 (SCHATTE-LANZ) airfoil Max thickness 6.5% at 19.9% chord. Max camber 3.5% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 235 (SCHTTE-LANZ) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121900 0.0203900
0.0245900 0.0264800
0.0494300 0.0369600
0.0743000 0.0453400
0.0991900 0.0526300
0.1490800 0.0598000
0.1990300 0.0631700
0.2989600 0.0674000
0.3989800 0.0662400
0.4990500 0.0619900
0.5991900 0.0523300
0.6993600 0.0416700
0.7995700 0.0277100
0.8997700 0.0149600
0.9498800 0.0077300
1.0000000 0.0016000
0.0000000 0.0000000
0.0127400 -.0157000
0.0252600 -.0166100
0.0502000 -.0130300
0.0751600 -.0105400
0.1001300 -.0085600
0.1500800 -.0050900
0.2000300 -.0022200
0.2999600 0.0025200
0.3999300 0.0045600
0.4999400 0.0040000
0.5999600 0.0028400
0.6999700 0.0017800
0.7999800 0.0012200
0.9000000 0.0000600
0.9500200 -.0010700
1.0000000 -.0016000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe235-il | 50,000 | 9 | 36.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 50,000 | 5 | 37.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 9 | 52.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 5 | 48 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 9 | 60.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 5 | 57.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 9 | 73.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 5 | 68.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 9 | 80.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 5 | 81.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||