|
|
Comparing Airfoils
NACA 63-015A AIRFOIL
GOE 392 AIRFOIL
|
NACA 63-015A AIRFOIL |
GOE 392 AIRFOIL |
|---|
| Thickness (%) |
14.991 |
10.126 |
| Camber (%) |
0.051 |
4.838 |
| Trailing Edge Angle (%) |
17.196 |
12.243 |
| Lower Surface Flatness |
20.890 |
96.632 |
| Leading Edge Radius (%) |
1.945 |
2.468 |
Maximum Lift (CL) |
0.995 |
1.223 |
Maximum Lift Angle-of-Attack (deg) |
15.000 |
10.000 |
Maximum Lift-to-drag (L/D) |
36.354 |
78.829 |
Lift at Maximum Lift-to-drag |
0.769 |
1.051 |
Angle-of-Attack for Maximum Lift-to-drag (L/D) |
7.000 |
3.500 |
|
