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.

(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 66.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(supermarine371i-il) Supermarine 371-I (root)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord Max Cl/Cd 66.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n63210-il) NACA 63-210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Max Cl/Cd 66.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe776-il) GOE 776 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 776 airfoil Max thickness 25% at 30% chord Max camber 0% at 60% chord Max Cl/Cd 66.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s1010-il) S1010 HPV airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1010 HPV airfoil Max thickness 6% at 23.3% chord Max camber 0% at 0% chord Max Cl/Cd 66.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(rcsc2-il) NASA/LANGLEY RC-SC2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-SC2 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 0.5% at 62.5% chord Max Cl/Cd 66.2 at Re# 1,000,000 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 66.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(bacnlf-il) BOEING HSNLF AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord Max Cl/Cd 66.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ea81006-il) EPPLER EA 8(-1)-006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 8(-1)-006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 66 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rae103-il) RAE 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 66 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database