GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
GOE 281 (DAIMLER XII) AIRFOIL - Gottingen 281 (DAIMLER XII) airfoil
| Details | Dat file | Parser | |
|
(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord. Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 281 (DAIMLER XII) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124000 0.0165700
0.0248400 0.0266500
0.0497500 0.0425900
0.0746900 0.0533400
0.0996400 0.0607900
0.1495800 0.0717800
0.1995400 0.0783800
0.2995000 0.0850700
0.3995100 0.0838600
0.4995300 0.0791500
0.5995900 0.0688400
0.6996700 0.0564300
0.7997600 0.0412200
0.8998600 0.0233100
0.9499199 0.0128000
1.0000000 0.0026000
0.0000000 0.0000000
0.0125500 -.0084300
0.0250400 -.0074500
0.0500300 -.0056000
0.0750200 -.0040600
0.1000200 -.0029100
0.1500000 -.0005100
0.1999900 0.0012800
0.2999700 0.0046700
0.3999600 0.0070600
0.4999500 0.0076500
0.5999600 0.0075400
0.6999700 0.0051300
0.7999900 0.0022200
0.9000000 -.0000900
0.9500100 -.0016900
1.0000000 -.0026000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe281-il | 50,000 | 9 | 36.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 50,000 | 5 | 42.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 100,000 | 9 | 59 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 100,000 | 5 | 59.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 200,000 | 9 | 79.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 200,000 | 5 | 75.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 500,000 | 9 | 101.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 500,000 | 5 | 95.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 1,000,000 | 9 | 118.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 1,000,000 | 5 | 98.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||