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.

(goe703-il) GOE 703 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord Max Cl/Cd 57.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rae2822-il) RAE 2822 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 57.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rae69ck-il) RAE6-9CK AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 57.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hs1620-il) HAM-STD HS1-620 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 20% at 34% chord Max camber 4.1% at 44% chord Max Cl/Cd 57.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rae102-il) RAE 102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Max Cl/Cd 57.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 57.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe429-il) GOE 429 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 429 airfoil Max thickness 11.4% at 30% chord Max camber 0.2% at 10% chord Max Cl/Cd 57.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s4096-il) S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 12.5% at 34% chord Max camber 1.2% at 34% chord Max Cl/Cd 57.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0013 general aviation airfoil Max thickness 12.9% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 57.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e520-il) EPPLER 520 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E520 tailplane airfoil Max thickness 15% at 36.7% chord Max camber 0% at 0% chord Max Cl/Cd 57.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database