NACA66(215)-216
Direct link:
NACA66(215)-216
Info
|
DAT and DXF files
|
Shape
|
Venkataraman Fit
|
Applications (1)
|
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.
NACA66(215)-216
Family:
NACA 66-series
Max thickness:
16.0% at x = 45.80% chord
Max camber:
1.1% at x = 49.90% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
Wind Tunnel (NACA-TR-824)
Notes:
Coordinates transcribed from NACA-TR-824