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.

(usa40b-il) USA 40 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40B airfoil Max thickness 13.6% at 20% chord Max camber 4% at 40% chord Max Cl/Cd 56.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s807-nr) NREL's S807 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S807 root Max thickness 18% at 28.7% chord Max camber 1.9% at 78.3% chord Max Cl/Cd 56.4 at Re# 200,000 Source NWTC National WInd Technology Center
(ls421-il) NASA/LANGLEY LS(1)-0421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0421 general aviation airfoil Max thickness 20.9% at 40% chord Max camber 2.4% at 65% chord Max Cl/Cd 56.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe10k-il) GOE 10K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 10K airfoil Max thickness 3.9% at 50% chord Max camber 1.4% at 60% chord Max Cl/Cd 56.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s3-il) REPUBLIC S-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Republic S-3 airfoil (P-47 wing airfoil) Max thickness 11% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 56.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(e818-il) EPPLER 818 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E818 hydrofoil Max thickness 9.4% at 33.1% chord Max camber 2.8% at 67% chord Max Cl/Cd 56.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag09-il) AG09		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG09 airfoil Max thickness 4.9% at 17.4% chord Max camber 1.8% at 34.1% chord Max Cl/Cd 56.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh110-il) MH 110 10.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord Max Cl/Cd 56.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(stf86361-il) EPPLER STF 863-615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STF 863-615 airfoil Max thickness 14.7% at 44.7% chord Max camber 4.2% at 72.3% chord Max Cl/Cd 56.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Propfan Cruise Missile wing airfoil Max thickness 8.2% at 40% chord Max camber 1.3% at 50% chord Max Cl/Cd 56.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database