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.

(sc20404-il) NASA SC(2)-0404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord Max Cl/Cd 55.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s1014-il) S1014		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1014 HPV airfoil Max thickness 16.5% at 42.2% chord Max camber 0% at 0% chord Max Cl/Cd 54.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fxs02196-il) FX S 02-196 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 02-196 airfoil Max thickness 19.6% at 37.1% chord Max camber 3.7% at 43.5% chord Max Cl/Cd 54.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca23024-il) NACA 23024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23024 airfoil Max thickness 24% at 30.3% chord Max camber 2.9% at 1.3% chord Max Cl/Cd 54.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(stcyr171-il) St. CYR 171 (Royer)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 171 (Royer) airfoil Max thickness 11.1% at 30% chord Max camber 1.5% at 50% chord Max Cl/Cd 54.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(fx3-il) WORTMANN FX 3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord Max Cl/Cd 54.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(lwk80080-il) LWK 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-080 symmetrical airfoil Max thickness 8.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 54.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(cp-120-050-gn) Cambered plate C=12% T=5% R=1.1		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=12% Wall thickness=5% Radius=1.102 Max thickness 6.1% at 4% chord Max camber 9.9% at 47.9% chord Max Cl/Cd 53.7 at Re# 1,000,000 Source Generated
(naca001066-il) NACA 0010-66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord Max Cl/Cd 53.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe388-il) GOE 388 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 388 airfoil Max thickness 10.2% at 29.9% chord Max camber 5.4% at 39.9% chord Max Cl/Cd 53.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database