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.

(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Max Cl/Cd 64.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx71120-il) WORTMANN FX 71-120 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-120 airfoil Max thickness 12% at 25% chord Max camber 0% at 0% chord Max Cl/Cd 64.4 at Re# 1,000,000 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 64.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n12-il) N-12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-12 airfoil Max thickness 10.5% at 30% chord Max camber 0.2% at 15% chord Max Cl/Cd 64.4 at Re# 1,000,000 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 64.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(fx38153-il) FX 38-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord Max Cl/Cd 64.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(v13006-il) BOEING VERTOL V13006-.7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V13006-.7 rotorcraft airfoil Max thickness 6% at 30.2% chord Max camber 0.9% at 20.2% chord Max Cl/Cd 64.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n63010a-il) NACA 63A010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-010A airfoil Max thickness 10% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 64.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord Max Cl/Cd 64.2 at Re# 1,000,000 Source Generated
(goe409-il) GOE 409 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 409 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 64.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database