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.

(goe526-il) GOE 526 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 526 airfoil Max thickness 12.3% at 29.7% chord Max camber 4.1% at 39.7% chord Max Cl/Cd 119.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(gm15sm-il) GM15 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gilbert Morris GM15 F1C class free flight flapper airfoil Max thickness 6.7% at 20.5% chord Max camber 4.8% at 49.3% chord Max Cl/Cd 119.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe370-il) GOE 370 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 370 airfoil Max thickness 4.7% at 20% chord Max camber 5.7% at 40% chord Max Cl/Cd 119.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord Max Cl/Cd 119.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq3513-il) HQ 3.5/13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/13 R/C sailplane airfoil Max thickness 13% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 119.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(naca4415-il) NACA 4415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord Max Cl/Cd 119.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe419-il) GOE 419 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 419 airfoil Max thickness 5.3% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 119.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sa7038-il) SA7038		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7038 Max thickness 9.2% at 28.5% chord Max camber 3% at 42.5% chord Max Cl/Cd 119.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx61147-il) FX 61-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-147 airfoil Max thickness 14.8% at 33.9% chord Max camber 3.2% at 33.9% chord Max Cl/Cd 119.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s806a-nr) NREL's S806A Airfoil (modified line 35)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S806A tip Max thickness 11.5% at 45% chord Max camber 2.8% at 45% chord Max Cl/Cd 119.2 at Re# 1,000,000 Source NWTC National WInd Technology Center