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.

(n6h15-il) NACA 6-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-15 rotorcraft airfoil Max thickness 15.6% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 15.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe767-il) GOE 767 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 767 airfoil Max thickness 12% at 20% chord Max camber 1.5% at 20% chord Max Cl/Cd 15.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah83159-il) AH 83-159		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord Max Cl/Cd 15.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh92-il) MH 92 15.49%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord Max Cl/Cd 15.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(l7769-il) LISSAMAN 7769 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lissaman 7769 human powered aircraft airfoil Max thickness 11% at 30% chord Max camber 4.4% at 30% chord Max Cl/Cd 15.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(m9-il) NACA M9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord Max camber 7.2% at 30% chord Max Cl/Cd 15.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx3-il) WORTMANN FX 3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord Max Cl/Cd 15.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca0024-il) NACA 0024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0024 airfoil Max thickness 24% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 15.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx61168-il) FX 61-168 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-168 airfoil Max thickness 16.8% at 37.1% chord Max camber 3% at 37.1% chord Max Cl/Cd 15.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(trainer60-il) TRAINER60		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Planes R/C Trainer 60 airfoil Max thickness 18.3% at 27.1% chord Max camber 0.1% at 1.3% chord Max Cl/Cd 15.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database