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.

(naca642415-il) NACA 64(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe562-il) GOE 562 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 562 airfoil Max thickness 14.1% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe593-il) GOE 593 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 593 airfoil Max thickness 11.9% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(r1046-il) RONCZ 1046 VOYAGER CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1046 Voyager canard airfoil Max thickness 18.1% at 38% chord Max camber 6.7% at 42% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe389-il) GOE 389 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 389 airfoil Max thickness 10.3% at 29.8% chord Max camber 4% at 39.8% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(davis-il) Davis AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s3021-il) S3021-095-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3021 low Reynolds number airfoil Max thickness 9.5% at 30% chord Max camber 2.5% at 39.2% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(wb13535sm-il) WB-135/35 13.5% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Woody Blanchard WB135/35 R/C sailplane airfoil Max thickness 13.6% at 25% chord Max camber 3.8% at 50% chord Max Cl/Cd 101.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe393-il) GOE 393 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 393 airfoil Max thickness 6.1% at 19.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 101.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe361-il) GOE 361 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 361 airfoil Max thickness 6.8% at 20% chord Max camber 5.5% at 40% chord Max Cl/Cd 101.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database