Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

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.

(ah85l120-il) AH 85-L-120/17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord Max Cl/Cd 35 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx69pr281-il) FX 69-PR-281		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 69-PR-281 airfoil Max thickness 28.1% at 22.2% chord Max camber 5.6% at 50% chord Max Cl/Cd 35 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord Max camber 3.7% at 63.4% chord Max Cl/Cd 35 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ea81006-il) EPPLER EA 8(-1)-006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 8(-1)-006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 35 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(dbln526-il) SIKORSKY DBLN-526 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky DBLN-526 double ended rotorcraft airfoil Max thickness 26% at 50% chord Max camber 4% at 50% chord Max Cl/Cd 35 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(n2h15-il) NACA 2-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 34.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(cp-100-050-gn) Cambered plate C=10% T=5% R=1.3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=10% Wall thickness=5% Radius=1.3 Max thickness 7% at 4.2% chord Max camber 7.9% at 46.5% chord Max Cl/Cd 34.9 at Re# 200,000 Source Generated
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord Max Cl/Cd 34.7 at Re# 200,000 Source Generated
(ea61012-il) EPPLER EA 6(-1)-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 34.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe388-il) GOE 388 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 388 airfoil Max thickness 10.2% at 29.9% chord Max camber 5.4% at 39.9% chord Max Cl/Cd 34.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database