Similarly shaped airfoils to NACA64-714 a=0.8
Direct link:
NACA64-714 a=0.8
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.
NACA63-714 a=0.8
2.
NACA63A714
3.
NACA65-714 a=0.8
4.
NACA64A714
5.
NACA63A713
6.
NACA64-715 a=0.8
7.
NACA64-713 a=0.8
8.
NACA63-713 a=0.8
9.
NACA64A713
10.
NACA63-715 a=0.8
11.
NACA65-713 a=0.8
12.
NACA64-714 a=0.6
13.
NACA63-714 a=0.6
14.
NACA64-614 a=0.8
15.
EPPLER 210
16.
NACA63-614 a=0.8
17.
GA 37-614
18.
NACA65-715 a=0.8
19.
FX 84-W-140
20.
NACA65-714 a=0.6
21.
NACA65-614 a=0.8