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.

(goe498-il) GOE 498 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 498 airfoil Max thickness 15.9% at 29.4% chord Max camber 5.5% at 49.4% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e851-il) EPPLER E851 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E851 propeller airfoil Max thickness 9% at 37% chord Max camber 2.3% at 66.3% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca643618-il) NACA 64(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx84w097-il) FX 84-W-097		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-097 airfoil for use on wind turbines (W) Max thickness 9.7% at 33.9% chord Max camber 2.8% at 37.1% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh201-il) MH 201 13.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord Max camber 2.5% at 48.3% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe478-il) GOE 478 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 478 airfoil Max thickness 13.4% at 29.6% chord Max camber 4.3% at 39.6% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe746-il) GOE 746 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 746 airfoil Max thickness 9.8% at 30% chord Max camber 5% at 30% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe365-il) GOE 365 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 365 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.1% at 39.9% chord Max Cl/Cd 73.4 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 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe685-il) GOE 685 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 685 airfoil Max thickness 13.1% at 19.6% chord Max camber 4.2% at 49.5% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database