GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
GOE 199 (L.F.G. 5406) AIRFOIL - Gottingen 199 (L.F.G. 5406) airfoil
| Details | Dat file | Parser | |
|
(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL Gottingen 199 (L.F.G. 5406) airfoil Max thickness 7.3% at 30% chord. Max camber 5.2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 199 (L.F.G. 5406) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0124400 0.0206400
0.0249100 0.0296700
0.0498700 0.0444400
0.0748400 0.0556200
0.0998100 0.0656900
0.1497800 0.0774300
0.1997600 0.0833800
0.2997400 0.0884700
0.3997500 0.0876600
0.4997600 0.0816500
0.5997900 0.0724400
0.6998300 0.0585300
0.7998800 0.0419200
0.8999299 0.0242100
0.9499600 0.0149500
1.0000000 0.0055000
0.0000000 0.0000000
0.0125200 -.0083600
0.0250200 -.0067300
0.0500100 -.0029500
0.0750000 0.0008200
0.0999900 0.0033900
0.1499800 0.0081300
0.1999700 0.0116800
0.2999600 0.0151700
0.3999600 0.0154600
0.4999600 0.0141500
0.5999700 0.0103400
0.6999800 0.0052300
0.8000000 0.0002200
0.9000100 -.0031900
0.9500200 -.0056400
1.0000000 -.0055000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe199-il | 50,000 | 9 | 36.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 50,000 | 5 | 40.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 9 | 55.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 5 | 54.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 9 | 72 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 5 | 67.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 9 | 89.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 5 | 89.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 9 | 108.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 5 | 106.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||