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.

(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 67.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(npl9510-il) NPL 9510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord Max Cl/Cd 67.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(stcyr234-il) St. CYR 234 (Bartel 17-IC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 234 (Bartel 17-IC) airfoil Max thickness 16% at 20% chord Max camber 5.1% at 50% chord Max Cl/Cd 67.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa33-il) USA 33 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-33 airfoil Max thickness 14.2% at 29.9% chord Max camber 4.9% at 29.9% chord Max Cl/Cd 67.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca001264-il) NACA 0012-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 67.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(sc20010-il) NASA SC(2)-0010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 67.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 67.7 at Re# 1,000,000 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 67.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(oa206-il) ONERA OA206 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA206 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 6% at 31.8% chord Max camber 0.8% at 19.6% chord Max Cl/Cd 67.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe114-il) GOE 114 (MVA MK.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 114 (MVA MK.1) airfoil Max thickness 9.6% at 29.7% chord Max camber 3.5% at 49.7% chord Max Cl/Cd 67.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database