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.

(usa27m2-il) USA 27 mod. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27MOD airfoil Max thickness 13.3% at 30% chord Max camber 5% at 40% chord Max Cl/Cd 64.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah94156-il) AH 94-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-156 airfoil Max thickness 15.6% at 39.6% chord Max camber 3.6% at 41.5% chord Max Cl/Cd 64.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sm701-il) SM701		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord Max camber 3% at 60.3% chord Max Cl/Cd 64.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe368-il) GOE 368 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 368 airfoil Max thickness 7.7% at 14.9% chord Max camber 3.8% at 29.9% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e332-il) EPPLER 332 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E332 flying wing airfoil Max thickness 11.5% at 32.3% chord Max camber 3.1% at 22.6% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(pt40-il) PT40		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe147-il) GOE 147 (MVA H.6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 147 (MVA H.6) airfoil Max thickness 7.5% at 14.9% chord Max camber 3.8% at 29.9% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa32-il) USA 32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-32 airfoil Max thickness 14.7% at 19.8% chord Max camber 9.3% at 39.8% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e545-il) EPPLER 545 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E545 general aviation airfoil Max thickness 17.4% at 39.3% chord Max camber 1.8% at 29.9% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rhodesg32-il) Rhode St. Genese 32		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 32 airfoil Max thickness 11.9% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database