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.

(s9027-il) S9027 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord Max Cl/Cd 59.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 59.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca66206-il) NACA 66-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-206 airfoil Max thickness 6% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 59.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b540ols-il) BELL 540 AIRFOIL (MODIFIED NACA 0012)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell AH-1 rotor blade airfoil (operational loads survey) Max thickness 9.7% at 22.1% chord Max camber 0% at 0% chord Max Cl/Cd 59.4 at Re# 500,000 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 59.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(sc20518-il) NASA SC(2)-0518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord Max Cl/Cd 59.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(eh0009-il) EH 0.0/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 0.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 0% at 0% chord Max Cl/Cd 59.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b707a-il) BOEING 707 .08 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 11.4% at 24% chord Max camber 0.2% at 6% chord Max Cl/Cd 59.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(marsden-il) Marsden		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marsden airfoil Max thickness 27.9% at 31.6% chord Max camber 7.7% at 37.6% chord Max Cl/Cd 59.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s4096-il) S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 12.5% at 34% chord Max camber 1.2% at 34% chord Max Cl/Cd 59.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database