Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database list (N).

NACA 66-210 to NLF(1)-0115

Page 8 of 9     1 2 3 4 5 6 7 8 9     Next

(naca66210-il) NACA 66-210

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 66-210NACA 66-210 airfoil
Max thickness 10% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca662215-il) NACA 66(2)-215

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 66(2)-215NACA 66(2)-215 airfoil
Max thickness 15% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca662415-il) NACA 66(2)-415

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 66(2)-415NACA 66(2)-415 airfoil
Max thickness 15% at 45% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca663218-il) NACA 66(3)-218

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 66(3)-218NACA 66(3)-218 airfoil
Max thickness 18% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca663418-il) NACA 66(3)-418

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 66(3)-418NACA 66(3)-418 airfoil
Max thickness 18% at 44.9% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca664221-il) NACA 66(4)-221

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 66(4)-221NACA 66(4)-221 airfoil
Max thickness 21% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca671215-il) NACA 67

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 67NACA 67
Max thickness 15% at 50% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca747a315-il) NACA 747A315

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 747A315NACA 747A315 airfoil
Max thickness 15% at 40.2% chord
Max camber 2.5% at 35% chord
Source UIUC Airfoil Coordinates Database

(naca747a415-il) NACA 747A415

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA 747A415NACA 747A415 airfoil
Max thickness 15% at 40.2% chord
Max camber 3% at 35% chord
Source UIUC Airfoil Coordinates Database

(nacacyh-il) NACA CYH

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA CYHNACA CYH airfoil
Max thickness 11.7% at 30% chord
Max camber 2.8% at 40% chord
Source UIUC Airfoil Coordinates Database

(nacam12-il) NACA M12

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA M12NACA M12 airfoil
Max thickness 11.9% at 30% chord
Max camber 2% at 30% chord
Source UIUC Airfoil Coordinates Database

(nacam18-il) NACA M18

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA M18NACA M18 airfoil
Max thickness 12% at 30% chord
Max camber 4.1% at 30% chord
Source UIUC Airfoil Coordinates Database

(nacam2-il) NACA M2

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA M2NACA M2 airfoil
Max thickness 8.1% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(nacam3-il) NACA M3

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA M3NACA M3 airfoil
Max thickness 11.9% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(nacam6-il) NACA M6

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NACA M6NACA M6 airfoil
Max thickness 12% at 30% chord
Max camber 2.1% at 30% chord
Source UIUC Airfoil Coordinates Database

(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction)NASA SC(2)-0714 airfoil (Ref. NASA TP-2890)
Max thickness 13.9% at 37% chord
Max camber 2.5% at 80% chord
Source UIUC Airfoil Coordinates Database

(ncambre-il) ONERA NACA CAMBRE AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
ONERA NACA CAMBRE AIRFOILONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil
Max thickness 11.5% at 31.2% chord
Max camber 1.4% at 15.9% chord
Source UIUC Airfoil Coordinates Database

(nl722343-il) NLR-7223-43 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NLR-7223-43 AIRFOILNLR NLR-7223-43 transonic rotorcraft airfoil
Max thickness 8.6% at 38% chord
Max camber 1.3% at 74% chord
Source UIUC Airfoil Coordinates Database

(nl722362-il) NLR-7223-62 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NLR-7223-62 AIRFOILNLR NLR-7223-62 transonic rotorcraft airfoil
Max thickness 8.6% at 38% chord
Max camber 1.3% at 21.6% chord
Source UIUC Airfoil Coordinates Database

(nlf0115-il) NLF(1)-0115

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NLF(1)-0115NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil
Max thickness 15% at 44.1% chord
Max camber 1.8% at 30% chord
Source UIUC Airfoil Coordinates Database
Page 8 of 9     1 2 3 4 5 6 7 8 9     Next

Please see the source web site or designer for any license conditions.