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.

(naca2411-il) NACA 2.5411		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2411 airfoil Max thickness 11% at 29.5% chord Max camber 2.5% at 39.6% chord Max Cl/Cd 71.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m24-il) NACA M24 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-24 airfoil Max thickness 12% at 30.1% chord Max camber 6.3% at 30.1% chord Max Cl/Cd 71.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh26-il) MH 26 10.99%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 26 for F3D Pylon Racing (extended laminar flow) Max thickness 11% at 42.3% chord Max camber 1.4% at 42.3% chord Max Cl/Cd 71.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n8h12-il) NACA 8-H-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord Max Cl/Cd 71.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah93w174-il) AH 93-W-174		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-174 airfoil for use on wind turbines (W) Max thickness 17.4% at 33.9% chord Max camber 3.9% at 37.1% chord Max Cl/Cd 71.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe440-il) GOE 440 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 440 airfoil Max thickness 15.3% at 30% chord Max camber 9.7% at 40% chord Max Cl/Cd 71.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe309-il) GOE 309 (MVA H.41) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 309 (MVA H.41) airfoil Max thickness 8.4% at 30% chord Max camber 4.7% at 30% chord Max Cl/Cd 71.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa40-il) USA 40 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40 airfoil Max thickness 13.3% at 30% chord Max camber 4.2% at 40% chord Max Cl/Cd 71.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord Max camber 4.8% at 49.1% chord Max Cl/Cd 71.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx61184-il) FX 61-184 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-184 airfoil Max thickness 18.4% at 37.1% chord Max camber 3.1% at 62.9% chord Max Cl/Cd 71.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database