Similarly shaped airfoils to NACA66-217 a=0.0
Direct link:
NACA66-217 a=0.0
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.
NACA66-217 a=0.2
2.
NACA66-117 a=0.5
3.
NACA66-117 a=0.6
4.
NACA66-217 a=0.5
5.
NACA66-217
6.
NACA66-117 a=0.2
7.
NACA66-117 a=0.8
8.
NACA66-217 a=0.6
9.
NACA66A117
10.
NACA66-117 a=0.0
11.
NACA66A217
12.
NACA66-217 a=0.8
13.
NACA66-317 a=0.0
14.
NACA66-218 a=0.0
15.
NACA66-216 a=0.0
16.
NACA66-218 a=0.2
17.
NACA66-117
18.
NACA66-216 a=0.2
19.
NACA66-116 a=0.5
20.
NACA66-218 a=0.5
21.
NACA66-116 a=0.6