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.

(e555-il) EPPLER 555 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E555 general aviation airfoil Max thickness 16% at 31.9% chord Max camber 2.6% at 67.4% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63212-il) NACA 63-212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-212 airfoil Max thickness 12% at 34.9% chord Max camber 1.1% at 55% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq109-il) HQ 1.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m22-il) NACA M22 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-22 airfoil Max thickness 6.3% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(mh44-il) MH 44 9.66%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 44 for flying wings Max thickness 9.6% at 27.1% chord Max camber 1.5% at 36.9% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe548-il) GOE 548 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 548 airfoil Max thickness 11.9% at 40% chord Max camber 2.3% at 50% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag08-il) AG08		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG08 airfoil Max thickness 5.8% at 21% chord Max camber 1.7% at 40.4% chord Max Cl/Cd 32.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e377-il) EPPLER 377 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E377 ultralight airfoil Max thickness 3.9% at 8.4% chord Max camber 8.8% at 36.9% chord Max Cl/Cd 32.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database