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.

(s2091-il) S2091-101-83		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2091 low Reynolds number airfoil Max thickness 10.1% at 26% chord Max camber 3.7% at 39.5% chord Max Cl/Cd 99.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe492-il) GOE 492 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 492 airfoil Max thickness 6.2% at 29.9% chord Max camber 3.4% at 49.9% chord Max Cl/Cd 99.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe11k-il) GOE 11K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 11K airfoil Max thickness 7.5% at 50% chord Max camber 2.7% at 60% chord Max Cl/Cd 99.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s3025-il) S3025 9.38%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3025 low Reynolds number airfoil Max thickness 9.4% at 30.9% chord Max camber 3% at 44.9% chord Max Cl/Cd 99.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe29b-il) GOE 29B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 29B airfoil Max thickness 9.4% at 19.8% chord Max camber 6.5% at 29.8% chord Max Cl/Cd 99.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(e638-il) EPPLER 638 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E638 airfoil Max thickness 12.4% at 28.5% chord Max camber 4.4% at 24.5% chord Max Cl/Cd 99.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(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 99.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e553-il) EPPLER 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E553 general aviation airfoil Max thickness 18.1% at 31.8% chord Max camber 2.9% at 56.6% chord Max Cl/Cd 99.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd7037-il) SD7037-092-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord Max Cl/Cd 99.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(nacam18-il) NACA M18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 99.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database