GOE 423 AIRFOIL (goe423-il)
GOE 423 AIRFOIL - Gottingen 423 airfoil
| Details | Dat file | Parser | |
|
(goe423-il) GOE 423 AIRFOIL Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord. Max camber 5.1% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 423 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0118000 0.0286900
0.0240600 0.0388800
0.0486600 0.0552800
0.0733100 0.0695800
0.0980300 0.0810800
0.1475600 0.1002900
0.1972300 0.1140900
0.2968200 0.1307100
0.3967100 0.1353400
0.4969400 0.1258800
0.5973600 0.1085200
0.6978500 0.0885600
0.7984700 0.0631000
0.8991800 0.0336500
0.9495900 0.0170700
1.0000000 0.0008000
0.0000000 0.0000000
0.0130000 -.0204800
0.0256900 -.0282800
0.0508300 -.0342600
0.0759000 -.0369600
0.1009400 -.0385500
0.1509500 -.0389300
0.2009400 -.0388200
0.3008800 -.0363900
0.4008300 -.0339600
0.5007300 -.0299300
0.6006000 -.0247100
0.7004901 -.0200800
0.8003600 -.0149500
0.9002100 -.0087200
0.9501300 -.0053100
1.0000000 -.0008000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 423 AIRFOIL (goe423-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe423-il | 50,000 | 9 | 4.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 50,000 | 5 | 14.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 9 | 22.8 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 5 | 40.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 9 | 69.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 5 | 70.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 9 | 105.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 5 | 101.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 9 | 133.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 5 | 124.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||