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 (D).

Dormoy to DU 86-137/25 AIRFOIL

Page 2 of 2     1 2     Next

(dormoy-il) Dormoy

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
DormoyDormoy airfoil
Max thickness 9% at 30% chord
Max camber 2.9% at 40% chord
Source UIUC Airfoil Coordinates Database

(drgnfly-il) DRAGONFLY CANARD

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
DRAGONFLY CANARDDragonfly Canard airfoil
Max thickness 19.3% at 37.6% chord
Max camber 6.6% at 40.9% chord
Source UIUC Airfoil Coordinates Database

(dsma523a-il) DSMA-523A AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
DSMA-523A AIRFOILMcDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge
Max thickness 11% at 36% chord
Max camber 2.3% at 82% chord
Source UIUC Airfoil Coordinates Database

(dsma523b-il) DSMA-523B AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
DSMA-523B AIRFOILMcDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge
Max thickness 11% at 36% chord
Max camber 2.4% at 82% chord
Source UIUC Airfoil Coordinates Database

(du06-w-200-dt) DU 06-W-200 VAWT airfoil

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source file
DU 06-W-200  VAWT airfoilDU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT)
Max thickness 19.8% at 31.1% chord
Max camber 0.5% at 84.6% chord
Source TU Delft

(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
DELFT DU84-132V3 AIRFOIL (MEASURED)Airfoil measured from an ASW22 wing
Max thickness 13.6% at 33.9% chord
Max camber 3.1% at 45.3% chord
Source UIUC Airfoil Coordinates Database

(du8608418-il) DU86-084/18 8.44%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
DU86-084/18 8.44%Deflt University DU 86-084/18 low Reynolds number airfoil
Max thickness 8.5% at 36.9% chord
Max camber 1% at 45.8% chord
Source UIUC Airfoil Coordinates Database

(du861372-il) DU 86-137/25 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
DU 86-137/25 AIRFOILDelft University DU 86-137/25 Airfoil
Max thickness 13.6% at 41.6% chord
Max camber 0.3% at 1.6% chord
Source UIUC Airfoil Coordinates Database
Page 2 of 2     1 2     Next

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