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.

(fx60100sm-il) FX60-100 10.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% chord Max Cl/Cd 100.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(marske4-il) MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID tip airfoil (NACA 43012A*.833 hybrid) Max thickness 10.2% at 20% chord Max camber 2.8% at 15% chord Max Cl/Cd 100.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s809-nr) NREL's S809 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord Max Cl/Cd 100.6 at Re# 1,000,000 Source NWTC National WInd Technology Center
(arad10-il) ARA-D 10% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 10% thick propeller airfoil Max thickness 10% at 25% chord Max camber 4% at 35% chord Max Cl/Cd 100.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(kc135c-il) KC-135 BL200.76 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 10.6% at 40% chord Max camber 1.5% at 25% chord Max Cl/Cd 100.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(isa571-il) I.S.A. 571		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 571 airfoil Max thickness 7.4% at 30% chord Max camber 3.6% at 30% chord Max Cl/Cd 100.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe384-il) GOE 384 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 384 airfoil Max thickness 19.6% at 29.3% chord Max camber 6.9% at 39.3% chord Max Cl/Cd 100.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fxm2-il) WORTMANN FX M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX M2 airfoil Max thickness 8.4% at 19.6% chord Max camber 4.8% at 30.9% chord Max Cl/Cd 100.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ls417mod-il) NASA/LANGLEY LS(1)-0417MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0417MOD general aviation airfoil Max thickness 17% at 30.2% chord Max camber 2.3% at 20.2% chord Max Cl/Cd 100.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca747a315-il) NACA 747A315		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A315 airfoil Max thickness 15% at 40.2% chord Max camber 2.5% at 35% chord Max Cl/Cd 100.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database