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.

(joukowsk0021-jf) Joukovsky f=0% t=21%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 21% symmetrical airfoil Max thickness 21% at 26.6% chord Max camber 0% at 0% chord Max Cl/Cd 45.6 at Re# 200,000 Source Javafoil generated
(coanda1-il) Coanda 1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 1 airfoil Max thickness 5.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 45.4 at Re# 200,000 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 45.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e474-il) E474 (14.09%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E474 aerobatic aircraft airfoil Max thickness 14.1% at 21.5% chord Max camber 0% at 0% chord Max Cl/Cd 45.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe429-il) GOE 429 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 429 airfoil Max thickness 11.4% at 30% chord Max camber 0.2% at 10% chord Max Cl/Cd 45.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fxlv152-il) WORTMANN FX L V-152 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX L V-152 airfoil Max thickness 15.3% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 45.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc1095-il) SIKORSKY SC1095 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Balch SC1095 rotorcraft airfoil Max thickness 9.5% at 26.9% chord Max camber 0.8% at 26.9% chord Max Cl/Cd 45.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s9026-il) S9026 (9.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane Max thickness 9.5% at 27.3% chord Max camber 0% at 0% chord Max Cl/Cd 45.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s817-nr) NREL's S817 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S817 tip 16.0% Dia=30 to 50 m Re=3.0E+6 Clmax(S)=1.10 Clmax(R)=1.08 Restrained max lift coef Max thickness 16% at 51.1% chord Max camber 2.8% at 41.1% chord Max Cl/Cd 45.3 at Re# 200,000 Source NWTC National WInd Technology Center
(goe459-il) GOE 459 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 459 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 45.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database