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.

(raf69-il) RAF 69 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-69 airfoil Max thickness 20.6% at 30% chord Max camber 1.7% at 50% chord Max Cl/Cd 88.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e858-il) EPPLER 858 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E858 propeller airfoil Max thickness 22.7% at 26.6% chord Max camber 4.7% at 44.3% chord Max Cl/Cd 88.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rg14a147-il) RG 14A-1.4/7.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14A-1.4/7.0 airfoil Max thickness 7% at 29.7% chord Max camber 1.4% at 34.3% chord Max Cl/Cd 88 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ncambre-il) ONERA NACA CAMBRE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord Max camber 1.4% at 15.9% chord Max Cl/Cd 88 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag03-il) AG03 (flat aft bottom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG03 (flat aft bottom) airfoil Max thickness 6.2% at 25.7% chord Max camber 2% at 33.1% chord Max Cl/Cd 88 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe491-il) GOE 491 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 491 airfoil Max thickness 4.9% at 20% chord Max camber 2.9% at 30% chord Max Cl/Cd 88 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc1095r8-il) SIKORSKY SC1094R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Velkoff SC1095 R8 rotorcraft airfoil Max thickness 9.3% at 26.5% chord Max camber 2.1% at 20.5% chord Max Cl/Cd 88 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sg6041-il) SG6041		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6041 wind turbine airfoil (high L/D) Max thickness 10% at 34.9% chord Max camber 1.6% at 49.7% chord Max Cl/Cd 88 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(nl722362-il) NLR-7223-62 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 21.6% chord Max Cl/Cd 87.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ames03-il) NASA/AMES A-03 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord Max Cl/Cd 87.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database