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.

(dae11-il) DAE-11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord Max camber 6.6% at 44.4% chord Max Cl/Cd 132.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah94145-il) AH 94-145		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-145 airfoil Max thickness 14.6% at 38.9% chord Max camber 5.6% at 44.6% chord Max Cl/Cd 132.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ch10sm-il) CH10 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil Max thickness 12.8% at 30.6% chord Max camber 10.2% at 49.3% chord Max Cl/Cd 132.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe500-il) GOE 500 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 500 airfoil Max thickness 10% at 30% chord Max camber 6% at 50% chord Max Cl/Cd 131.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(davissm-il) davissm		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Davis 3R F1B free flight airfoil (smoothed) Max thickness 5.9% at 30.6% chord Max camber 5.9% at 45.4% chord Max Cl/Cd 131.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe227-il) GOE 227 (MVA H.37) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 227 (MVA H.37) airfoil Max thickness 14.6% at 25% chord Max camber 7.8% at 50% chord Max Cl/Cd 131.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx76mp140-il) FX 76-MP-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-140 airfoil Max thickness 14.1% at 33.9% chord Max camber 7.1% at 46.7% chord Max Cl/Cd 131.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx74080-il) WORTMANN FX 74-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 74-080 airfoil Max thickness 8.2% at 43.5% chord Max camber 4.3% at 46.7% chord Max Cl/Cd 131.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh114-il) MH 114 13.02%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 114 for a propeller for ultralight Max thickness 13% at 28.1% chord Max camber 6.4% at 50% chord Max Cl/Cd 131.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh115-il) MH 115 11.06%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 115 for a propeller for ultralight Max thickness 11.1% at 29.8% chord Max camber 5.5% at 46% chord Max Cl/Cd 130.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database