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.

(defcnd2-il) DEFIANT CANARD BL110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL110 airfoil Max thickness 14.7% at 28.6% chord Max camber 3.8% at 28.6% chord Max Cl/Cd 117.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx63110-il) FX 63-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-110 airfoil Max thickness 11% at 30.8% chord Max camber 4.3% at 50% chord Max Cl/Cd 117.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe325-il) GOE 325 (PFALZ 54) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 325 (Pfalz 54) airfoil Max thickness 8.2% at 20% chord Max camber 4.6% at 30% chord Max Cl/Cd 117.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord Max Cl/Cd 117.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq3012-il) HQ 3.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 117.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe314-il) GOE 314 (HANSA-BRANDENBURG) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 314 (Hansa-Brandenburg) airfoil Max thickness 8% at 29.9% chord Max camber 4.7% at 29.9% chord Max Cl/Cd 117.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe288-il) GOE 288 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 288 airfoil Max thickness 17.4% at 29.3% chord Max camber 5.5% at 39.3% chord Max Cl/Cd 117.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe593-il) GOE 593 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 593 airfoil Max thickness 11.9% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 117.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e333-il) EPPLER 333 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E333 flying wing airfoil Max thickness 11.7% at 31.3% chord Max camber 3.5% at 26.4% chord Max Cl/Cd 117.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s822-nr) NREL's S822 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord Max camber 1.8% at 59.5% chord Max Cl/Cd 117.1 at Re# 1,000,000 Source NWTC National WInd Technology Center