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.

(goe115-il) GOE 115 (MVA MK.2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 115 (MVA MK.2) airfoil Max thickness 9.7% at 29.7% chord Max camber 3.7% at 39.7% chord Max Cl/Cd 132 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e639-il) EPPLER 639 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E639 airfoil Max thickness 12.6% at 29.2% chord Max camber 4.8% at 29.2% chord Max Cl/Cd 131.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m20-il) NACA M20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-20 airfoil Max thickness 8.2% at 30% chord Max camber 6.1% at 30% chord Max Cl/Cd 131.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e1200-il) EPPLER 1200 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1200 general aviation airfoil Max thickness 16.9% at 36.1% chord Max camber 3.5% at 50.2% chord Max Cl/Cd 131.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx6617a2-il) FX 66-17AII-182 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17AII-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord Max Cl/Cd 131.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord Max Cl/Cd 131.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx84w127-il) FX 84-W-127		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-127 airfoil for use on wind turbines (W) Max thickness 12.8% at 33.9% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 131.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e432-il) EPPLER 432 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E432 sailplane airfoil Max thickness 16% at 37.4% chord Max camber 4.5% at 37.4% chord Max Cl/Cd 131.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq300gd2-il) HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	DFVLR/Braunschweig Horstmann and Quast HQ-300 GD(MOD 2) sailplane airfoil Max thickness 16.6% at 39.1% chord Max camber 3.9% at 39.1% chord Max Cl/Cd 131.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sp4621hp-po) SP4621HP		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Saab-Pimenta High Performance low TE noise 100 m Diameter Wind Turbine Main Airfoil Max thickness 21.1% at 36.5% chord Max camber 3.9% at 64.1% chord Max Cl/Cd 131.6 at Re# 1,000,000 Source Poli-Wind. University of Sao Paulo