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.

(fx79l120-il) FX 79-L-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-120 symmetrical airfoil Max thickness 12.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 74.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rc1264c-il) NASA/LANGLEY RC12-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 12-64C rotorcraft airfoil Max thickness 12% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 74.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah93w300-il) AH 93-W-300		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-300 airfoil for use on wind turbines (W) Max thickness 30% at 27.9% chord Max camber 1.6% at 72.1% chord Max Cl/Cd 74.8 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 74.8 at Re# 1,000,000 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 74.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(rae100-il) RAE 100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Max Cl/Cd 74.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca0021-il) NACA 0021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0021 airfoil Max thickness 21% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 74.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n0009sm-il) NACA-0009 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 74.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20410-il) NASA SC(2)-0410 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0410 airfoil (NASA TP-2969) Max thickness 10% at 38% chord Max camber 1.1% at 85% chord Max Cl/Cd 74.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh33-il) MH33		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 33 for F3E and F3B Max thickness 7.3% at 29.3% chord Max camber 1.1% at 43.9% chord Max Cl/Cd 74.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database