GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
GOE 275 (DAIMLER VI) AIRFOIL - Gottingen 275 (DAIMLER VI) airfoil
| Details | Dat file | Parser | |
|
(goe275-il) GOE 275 (DAIMLER VI) AIRFOIL Gottingen 275 (DAIMLER VI) airfoil Max thickness 7.7% at 19.9% chord. Max camber 4.7% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 275 (DAIMLER VI) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123100 0.0240000
0.0247200 0.0347000
0.0496100 0.0483000
0.0745300 0.0575000
0.0994700 0.0657100
0.1493900 0.0757100
0.1993300 0.0825100
0.2993100 0.0855200
0.3993300 0.0831300
0.4993800 0.0769400
0.5994500 0.0676600
0.6995500 0.0561700
0.7996700 0.0409800
0.8998200 0.0226900
0.9499000 0.0128900
1.0000000 0.0000000
0.0000000 0.0000000
0.0125600 -.0080000
0.0250500 -.0066000
0.0500300 -.0033900
0.0750100 -.0015900
0.1000000 -.0003900
0.1499800 0.0027100
0.1999600 0.0052200
0.2999300 0.0087300
0.3999100 0.0106400
0.4999100 0.0114500
0.5999100 0.0111600
0.6999199 0.0103700
0.7999400 0.0079800
0.8999700 0.0039900
0.9499800 0.0022900
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 275 (DAIMLER VI) AIRFOIL (goe275-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe275-il | 50,000 | 9 | 34.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 50,000 | 5 | 40.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 100,000 | 9 | 53.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 100,000 | 5 | 55.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 200,000 | 9 | 72 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 200,000 | 5 | 73.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 500,000 | 9 | 99.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 500,000 | 5 | 94.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 1,000,000 | 9 | 118.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 1,000,000 | 5 | 106.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||