Similarly shaped airfoils to NACA64-511 a=0.6
Direct link:
NACA64-511 a=0.6
Info
|
DAT and DXF files
|
Shape
|
Venkataraman Fit
|
Applications (0)
|
Similarly shaped airfoils
Plain Flapped Shapes:
25% flap chord
|
30% flap chord
|
35% flap chord
|
40% flap chord
Basic Data:
c
l
vs α
|
c
d
vs α
|
c
m
vs α
|
c
l
/c
d
vs α
|
c
d
vs c
l
|
c
l
/c
d
vs c
l
|
c
l
vs c
d
|
c
m
vs c
l
|
Curve fits
|
Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects:
c
l
vs α
|
c
d
vs α
|
c
m
vs α
|
c
l
/c
d
vs α
|
c
d
vs c
l
|
c
l
/c
d
vs c
l
|
c
l
vs c
d
|
c
m
vs c
l
Roughness Effects:
c
l
vs α
|
c
d
vs α
|
c
m
vs α
|
c
l
/c
d
vs α
|
c
d
vs c
l
|
c
l
/c
d
vs c
l
|
c
l
vs c
d
|
c
m
vs c
l
Plain Flap Effects:
c
l,max
vs flap deflection:
all flap chords
|
25% flap chord
|
30% flap chord
|
35% flap chord
|
40% flap chord
Plain Flap Effects:
c
l
vs α for various flap deflections:
25% flap chord
|
30% flap chord
|
35% flap chord
|
40% flap chord
Plain Flap Effects:
c
m
vs α for various flap deflections:
25% flap chord
|
30% flap chord
|
35% flap chord
|
40% flap chord
Plain Flap Effects:
c
d
vs α for various flap deflections:
25% flap chord
|
30% flap chord
|
35% flap chord
|
40% flap chord
Disclaimer:
All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
1.
NACA63-511 a=0.6
2.
NACA64-511 a=0.5
3.
NACA63-511 a=0.5
4.
GA 37-411
5.
NACA65-511 a=0.6
6.
GA 35-411
7.
GA 35A411
8.
NACA65-511 a=0.5
9.
GA 40-411
10.
GA 40A411
11.
GA 37A411
12.
NACA64-511 a=0.8
13.
NACA63-511 a=0.8
14.
K3311 (original)
15.
K3311 (smoothed)
16.
S4158
17.
NACA64-512 a=0.6
18.
NACA64-510 a=0.6
19.
NACA65-510 a=0.6
20.
NACA63-510 a=0.6
21.
NACA63-512 a=0.6