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.

(rae5214-il) RAE 5214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5214 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.4% at 69.1% chord Max Cl/Cd 35.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(marske2-il) MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IA airfoil (NACA 23112/43012A hybrid) Max thickness 12.1% at 25% chord Max camber 2.7% at 15% chord Max Cl/Cd 35.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah80140-il) AH 80-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord Max camber 4.4% at 33.9% chord Max Cl/Cd 35.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca23021-il) NACA 23021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23021 airfoil Max thickness 21% at 30% chord Max camber 1.9% at 10% chord Max Cl/Cd 35.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx79w151a-il) FX 79-W-151 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-W-151 airfoil for use on wind turbines (W) A Max thickness 15.2% at 33.9% chord Max camber 3.8% at 37.1% chord Max Cl/Cd 35.6 at Re# 100,000 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 35.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s821-nr) NREL's S821 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S821 root 24.0% Dia=10 to 20 m Re=8.0E+5 Clmax(S)=1.40 Clmax(R)=1.35 Restrained max lift coef Max thickness 24.2% at 24.6% chord Max camber 2.6% at 77.6% chord Max Cl/Cd 35.6 at Re# 100,000 Source NWTC National WInd Technology Center
(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 35.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa35a-il) USA 35 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35A airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 35.6 at Re# 100,000 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 35.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database