Similarly shaped airfoils to NACA66-411 a=0.6
Direct link:
NACA66-411 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.
NACA66-411 a=0.5
2.
NACA66-411 a=0.8
3.
NACA66A411
4.
NACA66-511
5.
NACA67-411 a=0.6
6.
NACA65A411
7.
NACA67-411 a=0.5
8.
NACA65-411 a=0.6
9.
NACA66-412 a=0.6
10.
NACA66-410 a=0.6
11.
NACA67-410 a=0.6
12.
NACA65-411 a=0.5
13.
NACA66-410 a=0.5
14.
NACA67-410 a=0.5
15.
NACA66-412 a=0.5
16.
NACA67-411 a=0.8
17.
NACA67A411
18.
NACA65-412 a=0.6
19.
NACA65-412 a=0.5
20.
NACA65-411 a=0.8
21.
NACA66-410 a=0.8