0920
OTHER: Aerodynamics -
Airfoil - Wortmann FX 74-CL5-140
Drawing:
Notes:
This airfoil is being considered for the UniCopter's horizontal stabilizer.
Aerodynamics:
Alpha @ zero lift
[AlphaL0] came from NVFoil calculation.|
Airfoil |
|
Wortmann FX 74-CL5-140 |
Wortmann FX 74 Mods |
|
Alpha @ zero lift [AlphaL0] |
|
|
|
|
Thickness |
|
0.1405 |
|
|
Leading edge radius |
|
0.0182 |
|
|
Camber |
|
0.0980 |
|
|
Trailing edge angle[deg] |
|
342.6357 |
|
|
Alpha |
Cl |
Cd |
Cm |
Ctr of Lift |
|
-2 |
1.243 |
0.011 |
-0.289 |
50 |
|
0 |
1.441 |
0.008 |
-0.294 |
45 |
|
2 |
1.670 |
0.004 |
-0.298 |
43 |
|
4 |
1.900 |
0.001 |
-0.302 |
41 |
|
6 |
2.130 |
-0.002 |
-0.306 |
40 |
|
8 |
2.359 |
-0.004 |
-0.309 |
38 |
|
10 |
2.588 |
-0.005 |
-0.313 |
37 |
|
12 |
||||
|
14 |
||||
|
16 |
Prouty shows the Cl Max as being 2.4. Does this mean that the airfoil starts to stall at 10º angle of attack?
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Last Revised: July 10, 2001