Airfoil Tools
Search 1638 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search (Symmetrical)

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

Optional
Optional
Optional
Optional. Symmetrical airfoils = 0
Optional


(e171-il) (Dicke 12.28%)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
(Dicke 12.28%)Eppler E171 low Reynolds number airfoil
Max thickness 12.3% at 32.4% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(e168-il) E168 (12.45%)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
E168  (12.45%)Eppler E168 low Reynolds number airfoil
Max thickness 12.4% at 26.7% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(e836-il) EPPLER E836 HYDROFOIL AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
EPPLER E836 HYDROFOIL AIRFOILEppler E836 hydrofoil
Max thickness 12.6% at 42.8% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(raf30-il) RAF 30 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
RAF 30 AIRFOILRAF-30 airfoil
Max thickness 12.6% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(goe409-il) GOE 409 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 409 AIRFOILGottingen 409 airfoil
Max thickness 12.7% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(goe459-il) GOE 459 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 459 AIRFOILGottingen 459 airfoil
Max thickness 12.7% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(ultimate-il) ULTIMATE

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
ULTIMATECarl Goldberg R/C Ultimate Bipe airfoil
Max thickness 12.8% at 34.2% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NASA/LANGLEY LS(1)-0013 AIRFOILNASA/Langley LS(1)-0013 general aviation airfoil
Max thickness 12.9% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(goe411-il) GOE 411 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
GOE 411 AIRFOILGottingen 411 airfoil
Max thickness 13.2% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(stcyr172-il) St. CYR 172 (Royer)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
St. CYR 172 (Royer)St. CYR 172 (Royer) airfoil
Max thickness 13.6% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Page 9 of 14     1 2 3 4 5 6 7 8 9 10 11 12 13 14     Next


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