GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL - Gottingen 304 (Friedrichshafen G02) airfoil
| Details | Dat file | Parser | |
|
(goe304-il) GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL Gottingen 304 (Friedrichshafen G02) airfoil Max thickness 9% at 29.8% chord. Max camber 6.3% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121000 0.0269800
0.0244400 0.0379600
0.0491900 0.0542300
0.0740300 0.0651000
0.0989000 0.0742700
0.1487000 0.0873100
0.1985700 0.0960500
0.2984300 0.1057300
0.3984200 0.1065200
0.4985100 0.1004000
0.5986900 0.0880900
0.6989400 0.0714800
0.7992401 0.0513700
0.8995800 0.0282600
0.9497700 0.0153000
1.0000000 0.0011500
0.0000000 0.0000000
0.0127100 -.0142100
0.0252300 -.0156300
0.0501700 -.0117500
0.0751200 -.0078800
0.1000600 -.0039100
0.1499600 0.0027300
0.1998800 0.0082700
0.2997600 0.0159500
0.3997000 0.0199400
0.4996900 0.0207200
0.5997100 0.0195100
0.6997800 0.0148900
0.7998500 0.0098800
0.8999400 0.0040600
0.9499800 0.0013100
1.0000000 -.0011500
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe304-il | 50,000 | 9 | 33.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 50,000 | 5 | 38.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 100,000 | 9 | 62 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 100,000 | 5 | 64.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 200,000 | 9 | 88.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 200,000 | 5 | 86.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 500,000 | 9 | 122.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 500,000 | 5 | 109.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 1,000,000 | 9 | 145.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 1,000,000 | 5 | 117.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||