GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
GOE 174 (ALBATROS 5020) AIRFOIL - Gottingen 174 (Albatros 5020) airfoil
| Details | Dat file | Parser | |
|
(goe174-il) GOE 174 (ALBATROS 5020) AIRFOIL Gottingen 174 (Albatros 5020) airfoil Max thickness 8.6% at 19.9% chord. Max camber 5.6% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 174 (ALBATROS 5020) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123600 0.0212800
0.0247900 0.0317700
0.0496900 0.0465400
0.0746000 0.0599000
0.0995300 0.0689700
0.1494400 0.0828100
0.1993800 0.0913500
0.2993500 0.0967200
0.3993600 0.0945000
0.4994200 0.0863700
0.5995000 0.0737500
0.6995900 0.0600200
0.7997100 0.0425000
0.8998400 0.0243700
0.9499000 0.0147100
1.0000000 0.0014500
0.0000000 0.0000000
0.0125500 -.0081200
0.0250500 -.0080300
0.0500500 -.0072600
0.0750400 -.0058900
0.1000200 -.0041200
0.1500000 -.0000900
0.1999600 0.0055500
0.2999100 0.0126200
0.3998900 0.0169000
0.4998800 0.0175700
0.5999000 0.0152500
0.6999199 0.0124200
0.7999400 0.0090000
0.8999700 0.0037700
0.9499900 0.0008100
1.0000000 -.0014500
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe174-il | 50,000 | 9 | 29.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe174-il | 50,000 | 5 | 40 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe174-il | 100,000 | 9 | 53.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe174-il | 100,000 | 5 | 59 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe174-il | 200,000 | 9 | 75.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe174-il | 200,000 | 5 | 76.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe174-il | 500,000 | 9 | 104.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe174-il | 500,000 | 5 | 101.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe174-il | 1,000,000 | 9 | 125.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe174-il | 1,000,000 | 5 | 117.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||