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.

(goe441-il) GOE 441 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 441 airfoil Max thickness 16% at 29.5% chord Max camber 7.7% at 39.5% chord Max Cl/Cd 45.6 at Re# 100,000 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 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe228-il) GOE 228 (MVA H.38) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 228 (MVA H.38) airfoil Max thickness 17.9% at 29.4% chord Max camber 7% at 49.4% chord Max Cl/Cd 45.6 at Re# 100,000 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 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n8h12-il) NACA 8-H-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord Max Cl/Cd 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(eh1590-il) EH 1.5/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.5/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1.5% at 25.9% chord Max Cl/Cd 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e502-il) EPPLER 502 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E502 general purpose airfoil Max thickness 15.6% at 42.1% chord Max camber 1.5% at 32.3% chord Max Cl/Cd 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rhodesg34-il) Rhode St. Genese 34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 34 airfoil Max thickness 14.1% at 30% chord Max camber 4.6% at 40% chord Max Cl/Cd 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(oa212-il) ONERA OA212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12% at 31.8% chord Max camber 2.3% at 31.8% chord Max Cl/Cd 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e337-il) EPPLER 337 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E337 flying wing airfoil Max thickness 13.1% at 32% chord Max camber 3.2% at 22.4% chord Max Cl/Cd 45.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database