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.

(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 59.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe346-il) GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 346 (Friedrichshafen-Staaken) airfoil Max thickness 5.7% at 39.9% chord Max camber 3.8% at 39.9% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe547-il) GOE 547 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 547 airfoil Max thickness 10.5% at 29.7% chord Max camber 4% at 49.7% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe602m-il) GOE 602 MOD. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 602 MOD airfoil Max thickness 9.6% at 30% chord Max camber 3.8% at 50% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe287-il) GOE 287 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 287 airfoil Max thickness 8.9% at 29.9% chord Max camber 4.9% at 39.9% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(hor07-il) ONERA HOR07 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 7.2% at 23.2% chord Max camber 4.5% at 39.6% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe101-il) GOE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 101 airfoil Max thickness 6.9% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq258-il) HQ 2.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe311-il) GOE 311 (MVA H.43) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 311 (MVA H.43) airfoil Max thickness 8.4% at 19.9% chord Max camber 6.1% at 39.9% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe602m-il) GOE 602 MOD. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 602 MOD airfoil Max thickness 9.6% at 30% chord Max camber 3.8% at 50% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database