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.

(n2414-il) NACA 2414		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2414 airfoil Max thickness 14% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 79.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(arad13-il) ARA-D 13% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord Max Cl/Cd 79.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e1213-il) EPPLER 1213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1213 general aviation airfoil Max thickness 17.4% at 22.1% chord Max camber 2.1% at 35.1% chord Max Cl/Cd 79.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(as5045-il) AS5045 (15%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil Max thickness 15% at 37.5% chord Max camber 1% at 27.2% chord Max Cl/Cd 79.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf34-il) RAF 34 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-34 airfoil Max thickness 12.6% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 79.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe09k-il) GOE 9K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord Max Cl/Cd 79.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe681-il) GOE 681 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 681 airfoil Max thickness 16.8% at 29.2% chord Max camber 4.4% at 39.2% chord Max Cl/Cd 79.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq2090sm-il) HQ-2.0/9 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/9 R/C sailplane airfoil (smoothed) Max thickness 9% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 79.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(bw3-il) Bergey BW-3 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bergey BW-3 wind turbine airfoil (smoothed) Max thickness 5% at 7.4% chord Max camber 5.7% at 45.4% chord Max Cl/Cd 79.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe566-il) GOE 566 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 566 airfoil Max thickness 8.7% at 30% chord Max camber 2.6% at 40% chord Max Cl/Cd 79.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database