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.

(goe505-il) GOE 505 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 505 airfoil Max thickness 14% at 19.7% chord Max camber 5.9% at 39.7% chord Max Cl/Cd 68.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 68.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh20-il) MH 20 9.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 20 for F3D Pylon Racing Max thickness 9% at 32.2% chord Max camber 1.9% at 37.3% chord Max Cl/Cd 68.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(b737d-il) BOEING 737 OUTBOARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 737 airfoils Max thickness 10.8% at 40% chord Max camber 1.6% at 20% chord Max Cl/Cd 68.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe548-il) GOE 548 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 548 airfoil Max thickness 11.9% at 40% chord Max camber 2.3% at 50% chord Max Cl/Cd 68.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx73cl1152-il) FX 73-CL1-152		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-CL1-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.1% at 33.9% chord Max Cl/Cd 68.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(df101-il) DF 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 101 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.3% at 43.5% chord Max Cl/Cd 68.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sp4621hp-po) SP4621HP		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Saab-Pimenta High Performance low TE noise 100 m Diameter Wind Turbine Main Airfoil Max thickness 21.1% at 36.5% chord Max camber 3.9% at 64.1% chord Max Cl/Cd 68.7 at Re# 200,000 Source Poli-Wind. University of Sao Paulo
(hq159-il) HQ 1.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 68.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd5060-il) SD5060 (9.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD5060 low Reynolds number airfoil Max thickness 9.5% at 24.9% chord Max camber 2% at 48.5% chord Max Cl/Cd 68.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database