GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
GOE 280 (DAIMLER XI) AIRFOIL - Gottingen 280 (DAIMLER XI) airfoil
| Details | Dat file | Parser | |
|
(goe280-il) GOE 280 (DAIMLER XI) AIRFOIL Gottingen 280 (DAIMLER XI) airfoil Max thickness 7.9% at 30% chord. Max camber 4.5% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 280 (DAIMLER XI) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124500 0.0167300
0.0249200 0.0306700
0.0498800 0.0461300
0.0748400 0.0575000
0.0998300 0.0645700
0.1498000 0.0741000
0.1997800 0.0800400
0.2997700 0.0851100
0.3997700 0.0833800
0.4997900 0.0771500
0.5998200 0.0683200
0.6998500 0.0558900
0.7998900 0.0417600
0.8999400 0.0234300
0.9499600 0.0138600
1.0000000 0.0040000
0.0000000 0.0000000
0.0125200 -.0066700
0.0250200 -.0057300
0.0500100 -.0025600
0.0750000 -.0006000
0.1000000 0.0010700
0.1499900 0.0033000
0.1999900 0.0048400
0.2999800 0.0058100
0.3999800 0.0055800
0.4999900 0.0052500
0.5999900 0.0045200
0.6999900 0.0030400
0.8000000 0.0013600
0.9000000 -.0007700
0.9500100 -.0023300
1.0000000 -.0040000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe280-il | 50,000 | 9 | 37.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 50,000 | 5 | 41.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 9 | 55.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 100,000 | 5 | 56.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 9 | 72.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 200,000 | 5 | 70.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 9 | 91.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 500,000 | 5 | 79.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 9 | 98.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe280-il | 1,000,000 | 5 | 87.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||