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.

(goe342-il) GOE 342 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 342 airfoil Max thickness 5.4% at 20% chord Max camber 6.2% at 40% chord Max Cl/Cd 44.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe484-il) GOE 484 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 484 airfoil Max thickness 6.3% at 30% chord Max camber 5% at 50% chord Max Cl/Cd 44.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe417-il) GOE 417 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 417 airfoil Max thickness 6% at 20% chord Max camber 6.1% at 40% chord Max Cl/Cd 44.4 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 44.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sokolov-il) SOKOLOV AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sokolov R/C sailplane airfoil Max thickness 7.1% at 25% chord Max camber 6.3% at 50% chord Max Cl/Cd 44.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(a18sm-il) A18 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Archer A18 F1C free flight airfoil (smoothed) Max thickness 7.3% at 27.1% chord Max camber 3.8% at 49.3% chord Max Cl/Cd 44.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cr001sm-il) cr001sm		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Cody Robertson CR 001 R/C hand-launch low Reynolds number airfoil (smoothed) Max thickness 7.3% at 27.1% chord Max camber 4.1% at 45.4% chord Max Cl/Cd 44.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e58-il) EPPLER 58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E58 low Reynolds number airfoil Max thickness 5.6% at 30% chord Max camber 6.5% at 50% chord Max Cl/Cd 44.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe195-il) GOE 195 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 195 airfoil Max thickness 8.6% at 20% chord Max camber 5.1% at 50% chord Max Cl/Cd 44 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(a18-il) A18 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Archer A18 F1C free flight airfoil(original) Max thickness 7.3% at 30% chord Max camber 3.9% at 45% chord Max Cl/Cd 44 at Re# 50,000 Source UIUC Airfoil Coordinates Database