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.

(cp-140-050-gn) Cambered plate C=14% T=5% R=0.96		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=14% Wall thickness=5% Radius=0.963 Max thickness 5.5% at 3.6% chord Max camber 12.2% at 47.7% chord Max Cl/Cd 47.7 at Re# 1,000,000 Source Generated
(cp-180-050-gn) Cambered plate C=18% T=5% R=0.78		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=18% Wall thickness=5% Radius=0.784 Max thickness 5% at 3.2% chord Max camber 16.4% at 49.3% chord Max Cl/Cd 47.5 at Re# 1,000,000 Source Generated
(naca16009-il) NACA 16009		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 47.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca16018-il) NACA 16-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-018 airfoil Max thickness 18% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 47.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca16009-il) NACA 16009		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 47 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(rc0864c-il) NASA/LANGLEY RC08-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 08-64C rotorcraft airfoil Max thickness 8% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 46.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e864-il) EPPLER 864 STRUT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E864 strut airfoil Max thickness 38.8% at 32.7% chord Max camber 0.1% at 10.8% chord Max Cl/Cd 46.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20403-il) NASA SC(2)-0403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0403 airfoil (NASA TP-2969) Max thickness 3% at 36% chord Max camber 0.6% at 85% chord Max Cl/Cd 46.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(p51hroot-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 15.5% at 45% chord Max camber 1.3% at 47.5% chord Max Cl/Cd 46.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe445-il) GOE 445 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 445 airfoil Max thickness 6.4% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 46.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database