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.

(naca001035-il) NACA 0010-35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 18.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m22-il) NACA M22 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-22 airfoil Max thickness 6.3% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 18.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(raf69-il) RAF 69 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-69 airfoil Max thickness 20.6% at 30% chord Max camber 1.7% at 50% chord Max Cl/Cd 18.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe502-il) GOE 502 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 502 airfoil Max thickness 15.9% at 29.3% chord Max camber 6.1% at 49.4% chord Max Cl/Cd 18.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe09k-il) GOE 9K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord Max Cl/Cd 18.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ah93w145-il) AH 93-W-145		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-145 airfoil for use on wind turbines (W) Max thickness 14.5% at 33.9% chord Max camber 3.9% at 37.1% chord Max Cl/Cd 18.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nlr7301-il) NLR-7301 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord Max Cl/Cd 18.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e657-il) EPPLER 657 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E657 sailplane airfoil Max thickness 15.6% at 37% chord Max camber 4.6% at 47.6% chord Max Cl/Cd 18.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(dsma523a-il) DSMA-523A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge Max thickness 11% at 36% chord Max camber 2.3% at 82% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx78pk188-il) FX 78-PK-188/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-PK-188/20 variable geometry airfoil Max thickness 18.8% at 43.5% chord Max camber 2.4% at 50% chord Max Cl/Cd 18.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database