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.

(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 60.5 at Re# 500,000 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 60.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(npl9626-il) NPL 9626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9626 rotorcraft airfoil Max thickness 12.1% at 30.9% chord Max camber 0.7% at 30.9% chord Max Cl/Cd 60.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(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 60.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiie-il) GIII BL126 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.8% at 44.9% chord Max camber 1.2% at 29.9% chord Max Cl/Cd 60.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe775-il) GOE 775 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 775 airfoil Max thickness 21% at 30% chord Max camber 0% at 1.3% chord Max Cl/Cd 60.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(joukowsk0009-jf) Joukovsky f=0% t=9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 9% symmetrical airfoil Max thickness 9% at 25.5% chord Max camber 0% at 0% chord Max Cl/Cd 60.3 at Re# 500,000 Source Javafoil generated
(rae101-il) RAE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 60.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n13-il) N-13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-13 airfoil Max thickness 11.8% at 30% chord Max camber 0.1% at 95% chord Max Cl/Cd 60.2 at Re# 500,000 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 60.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database