Similarly shaped airfoils to NACA64-210 a=0.8
Direct link:
NACA64-210 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.
NACA63-210 a=0.8
2.
NACA64-210 a=0.6
3.
NACA63-210 a=0.6
4.
NACA64-210 a=0.5
5.
NACA64-210
6.
NACA63A210
7.
NACA63-210 a=0.5
8.
NACA65-210 a=0.8
9.
NACA63-210
10.
NACA64A210
11.
NACA64-310
12.
NACA65-210 a=0.6
13.
HQ 1.0/10
14.
NACA63-310
15.
SB96VS 9.75/1.25
16.
NACA65-210 a=0.5
17.
NACA65-210
18.
NACA64-210 a=0.2
19.
TP-CIEL-S
20.
NACA63-210 a=0.2
21.
NACA63A209