Similarly shaped airfoils to NACA65-417 a=0.0
Direct link:
NACA65-417 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.
NACA65-417 a=0.2
2.
NACA65-317 a=0.2
3.
NACA65-317 a=0.5
4.
GA 40-217
5.
GA 40A217
6.
NACA65-418 a=0.0
7.
NACA65-416 a=0.0
8.
NACA65-317 a=0.6
9.
NACA64-417 a=0.0
10.
NACA65-418 a=0.2
11.
NACA65-317 a=0.0
12.
NACA64-417 a=0.2
13.
NACA65-517 a=0.0
14.
GA 37A217
15.
NACA65-416 a=0.2
16.
NACA65-316 a=0.2
17.
NACA65-318 a=0.5
18.
NACA65-316 a=0.5
19.
NACA65-318 a=0.2
20.
NACA64-418 a=0.2
21.
NACA64-418 a=0.0