Similarly shaped airfoils to NACA65-710 a=0.0
Direct link:
NACA65-710 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.
NACA64-710 a=0.0
2.
NACA65-610 a=0.2
3.
NACA65-710 a=0.2
4.
NACA63-710 a=0.0
5.
NACA64-610 a=0.2
6.
NACA64-710 a=0.2
7.
NACA66-710 a=0.0
8.
NACA65-711 a=0.0
9.
NACA65-709 a=0.0
10.
NACA64-711 a=0.0
11.
NACA66-709 a=0.0
12.
NACA63-710 a=0.2
13.
NACA63-610 a=0.2
14.
NACA66-610 a=0.2
15.
NACA65-609 a=0.2
16.
NACA64-711 a=0.2
17.
NACA66-609 a=0.2
18.
NACA65-610 a=0.0
19.
NACA65-711 a=0.2
20.
NACA66-710 a=0.2
21.
NACA65-611 a=0.2