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.

(goe222-il) GOE 222 (MVA H.33) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 222 (MVA H.33) airfoil Max thickness 18.5% at 29.2% chord Max camber 7.2% at 49.2% chord Max Cl/Cd 47.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiii-il) GIII BL288 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 40% chord Max camber 1.3% at 25% chord Max Cl/Cd 47.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(kc135a-il) KC-135 BL52.44 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord Max camber 1.3% at 20% chord Max Cl/Cd 47.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx84w150-il) FX 84-W-150		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-150 airfoil for use on wind turbines (W) Max thickness 15% at 37.1% chord Max camber 4.2% at 40.2% chord Max Cl/Cd 47.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe207-il) GOE 207 (AVIATIK V8) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 207 (AVIATIK V8) airfoil Max thickness 8.8% at 19.9% chord Max camber 6.6% at 29.9% chord Max Cl/Cd 47.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ag44ct02r-il) AG44ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG44ct -02f airfoil Max thickness 7.3% at 24.6% chord Max camber 1.9% at 34.4% chord Max Cl/Cd 47.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s834-nr) NREL's S834 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S834 tip 15.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.00 Clmax(R)=1.02 High max lift coef Max thickness 15% at 39.5% chord Max camber 1.6% at 60% chord Max Cl/Cd 47.4 at Re# 100,000 Source NWTC National WInd Technology Center
(e403-il) EPPLER 403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E403 general purpose airfoil Max thickness 15% at 37.9% chord Max camber 3.2% at 75.5% chord Max Cl/Cd 47.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e542-il) EPPLER 542 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E542 general aviation airfoil Max thickness 16.9% at 41.3% chord Max camber 1.9% at 31.5% chord Max Cl/Cd 47.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx66h80-il) FX 66-H-80		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord Max Cl/Cd 47.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database