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.

(hor12-il) ONERA HOR12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 11.9% at 22.8% chord Max camber 3.7% at 46.2% chord Max Cl/Cd 97.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx05188-il) WORTMANN FX 05-188 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-188 airfoil Max thickness 18.8% at 37.1% chord Max camber 2.6% at 50% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe508-il) GOE 508 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 508 airfoil Max thickness 16.5% at 30% chord Max camber 5.6% at 40% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe92-il) GOE 92 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 92 airfoil Max thickness 8.8% at 30% chord Max camber 5.5% at 30% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(sd7032-il) SD7032-099-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa35a-il) USA 35 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35A airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(be50sm-il) BE50 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 23.8% chord Max camber 4% at 45.4% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf48-il) RAF-48 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-48 airfoil Max thickness 15% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 97.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(lds2-il) LDS-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord Max Cl/Cd 97.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database