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.

(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord Max Cl/Cd 61.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe604-il) GOE 604 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 604 airfoil Max thickness 17.8% at 29.3% chord Max camber 5.4% at 29.3% chord Max Cl/Cd 61.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe462-il) GOE 462 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 462 airfoil Max thickness 11% at 9.9% chord Max camber 13.4% at 29.9% chord Max Cl/Cd 61.2 at Re# 200,000 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 61.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STE 87(-3)-914 airfoil Max thickness 14.6% at 34.1% chord Max camber 4.2% at 58.3% chord Max Cl/Cd 61.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(s830-nr) NREL's S830 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef Max thickness 21% at 38.4% chord Max camber 4.4% at 70.5% chord Max Cl/Cd 61.1 at Re# 200,000 Source NWTC National WInd Technology Center
(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 61.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe417a-il) GOE 417A (GEW. PLATTE) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 417A (GEW. PLATTE) airfoil Max thickness 3.2% at 2.5% chord Max camber 5.9% at 40% chord Max Cl/Cd 61.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(defcnd3-il) DEFIANT CANARD BL145 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL145 airfoil Max thickness 11.5% at 28.6% chord Max camber 2.4% at 28.6% chord Max Cl/Cd 61.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord Max Cl/Cd 61 at Re# 200,000 Source UIUC Airfoil Coordinates Database