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.

(be50-il) BE50 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 25% chord Max camber 4.1% at 45% chord Max Cl/Cd 43.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e59-il) EPPLER 59 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E59 low Reynolds number airfoil Max thickness 5.6% at 25% chord Max camber 5.2% at 50% chord Max Cl/Cd 43.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe395-il) GOE 395 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 395 airfoil Max thickness 6.1% at 19.9% chord Max camber 7% at 49.9% chord Max Cl/Cd 43.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(be50sm-il) BE50 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 23.8% chord Max camber 4% at 45.4% chord Max Cl/Cd 43 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hs1708-il) HAM-STD HS1-708 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 7.9% at 22% chord Max camber 5% at 46% chord Max Cl/Cd 43 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe397-il) GOE 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 397 airfoil Max thickness 5.1% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 43 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e216-il) E216 (10.4%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E216 low Reynolds number airfoil Max thickness 10.4% at 26.2% chord Max camber 4.7% at 59% chord Max Cl/Cd 43 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe381-il) GOE 381 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 381 airfoil Max thickness 6.4% at 30% chord Max camber 5.8% at 30% chord Max Cl/Cd 43 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx63100-il) FX 63-100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-100 airfoil Max thickness 9.9% at 30.8% chord Max camber 4.3% at 50% chord Max Cl/Cd 43 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ma409-il) MA409 (original) (modified line 7)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Michael Achterberg MA409 F1C class free flight airfoil (original) Max thickness 6.8% at 25% chord Max camber 3.3% at 50% chord Max Cl/Cd 42.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database