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.

(naca4418-il) NACA 4418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4418 airfoil Max thickness 18% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe217-il) GOE 217 (MVA MK.12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 217 (MVA MK.12) airfoil Max thickness 19% at 29.2% chord Max camber 6.3% at 59.4% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rc12b3-il) NASA/LANGLEY RC-12(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-12(B)3 rotorcraft airfoil Max thickness 12% at 38% chord Max camber 2.2% at 34.3% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe503-il) GOE 503 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 503 airfoil Max thickness 15.6% at 29.7% chord Max camber 7% at 39.7% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa35-il) USA 35 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35 airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe223-il) GOE 223 (MVA H.34) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 223 (MVA H.34) airfoil Max thickness 18.8% at 29.1% chord Max camber 5.7% at 49.1% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s805a-nr) NREL's S805A Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S805A primary Max thickness 13.5% at 40% chord Max camber 2.1% at 35% chord Max Cl/Cd 67 at Re# 200,000 Source NWTC National WInd Technology Center
(tempest1-il) HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 37.5% semispan airfoil (NPL?) Max thickness 14.5% at 38.3% chord Max camber 1% at 40.4% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Max Cl/Cd 67 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 a=0.8 c(li)=0.2 airfoil Max thickness 11% at 39.9% chord Max camber 1.8% at 29.9% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database