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.

(e551-il) EPPLER 551 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E551 general aviation airfoil Max thickness 18.2% at 32.4% chord Max camber 2.8% at 57.1% chord Max Cl/Cd 14.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e344-il) EPPLER 344 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E344 flying wing airfoil Max thickness 14.7% at 29.9% chord Max camber 4.3% at 25% chord Max Cl/Cd 14.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca654421-il) NACA 65(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 airfoil Max thickness 21% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 14.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe311-il) GOE 311 (MVA H.43) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 311 (MVA H.43) airfoil Max thickness 8.4% at 19.9% chord Max camber 6.1% at 39.9% chord Max Cl/Cd 14.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx67k150-il) FX 67-K-150/17 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 67-K-150/17 airfoil Max thickness 15% at 40.2% chord Max camber 4.8% at 43.5% chord Max Cl/Cd 14.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ah80140-il) AH 80-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord Max camber 4.4% at 33.9% chord Max Cl/Cd 14.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh112-il) MH 112 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 112 for a propeller for ultralight (root) Max thickness 16.2% at 31.8% chord Max camber 6.7% at 48.5% chord Max Cl/Cd 14.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hs1430-il) HAM-STD HS1-430 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 30% at 34% chord Max camber 3% at 44% chord Max Cl/Cd 14.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s812-nr) NREL's S812 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S812 primary Max thickness 21% at 39.6% chord Max camber 1.6% at 77% chord Max Cl/Cd 14.2 at Re# 50,000 Source NWTC National WInd Technology Center
(s831-nr) NREL's S831 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord Max camber 5% at 53.1% chord Max Cl/Cd 14.2 at Re# 50,000 Source NWTC National WInd Technology Center