GOE 438 AIRFOIL (goe438-il)
GOE 438 AIRFOIL - Gottingen 438 airfoil
| Details | Dat file | Parser | |
|
(goe438-il) GOE 438 AIRFOIL Gottingen 438 airfoil Max thickness 11% at 29.8% chord. Max camber 3.8% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 438 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0119400 0.0223000
0.0241800 0.0326000
0.0488400 0.0462200
0.0735500 0.0578400
0.0983400 0.0664600
0.1480200 0.0792000
0.1978300 0.0869500
0.2976900 0.0924400
0.3977400 0.0904400
0.4979100 0.0834500
0.5982000 0.0719600
0.6985400 0.0584600
0.7989800 0.0409700
0.8994500 0.0219900
0.9497200 0.0112400
1.0000000 0.0000000
0.0000000 0.0000000
0.0128700 -.0146800
0.0255100 -.0203600
0.0505700 -.0227400
0.0755700 -.0226100
0.1005600 -.0224900
0.1505300 -.0212400
0.2005000 -.0199900
0.3004400 -.0174900
0.4003700 -.0149900
0.5003100 -.0124900
0.6002500 -.0099900
0.7001899 -.0075000
0.8001300 -.0050000
0.9000599 -.0025000
0.9500300 -.0012500
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 438 AIRFOIL (goe438-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe438-il | 50,000 | 9 | 24.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe438-il | 50,000 | 5 | 35.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe438-il | 100,000 | 9 | 49.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe438-il | 100,000 | 5 | 52.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe438-il | 200,000 | 9 | 68.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe438-il | 200,000 | 5 | 68.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe438-il | 500,000 | 9 | 95 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe438-il | 500,000 | 5 | 90.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe438-il | 1,000,000 | 9 | 115.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe438-il | 1,000,000 | 5 | 106 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||