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 46.3 at Re# 1,000,000 Source Generated
(us1000root-il) US1000ROOT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord Max camber 0% at 0% chord Max Cl/Cd 45.9 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 45.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(raf89-il) RAF 89 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-89 airfoil Max thickness 25% at 30% chord Max camber 1.6% at 50% chord Max Cl/Cd 45.6 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 45.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord Max Cl/Cd 45.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca001035-il) NACA 0010-35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 45.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(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 45 at Re# 1,000,000 Source Generated
(goe780-il) GOE 780 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 780 airfoil Max thickness 12% at 50% chord Max camber 1% at 40% chord Max Cl/Cd 44 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 43.8 at Re# 1,000,000 Source Generated