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.

(j5012-il) J5012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Jef Raskin (originator of the Apple Macintosh Project) J5012 airfoil Max thickness 12% at 34.5% chord Max camber 0% at 83.5% chord Max Cl/Cd 70.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe522-il) GOE 522 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 522 airfoil Max thickness 21.8% at 28.6% chord Max camber 5.2% at 48.7% chord Max Cl/Cd 70.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s9033-il) S9033 (7.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord Max Cl/Cd 70.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ea61012-il) EPPLER EA 6(-1)-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 70.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hs1620-il) HAM-STD HS1-620 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 20% at 34% chord Max camber 4.1% at 44% chord Max Cl/Cd 70.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(s835-nr) NREL's S835 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef Max thickness 21% at 30.5% chord Max camber 2.4% at 78% chord Max Cl/Cd 70.6 at Re# 1,000,000 Source NWTC National WInd Technology Center
(du8608418-il) DU86-084/18 8.44%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord Max camber 1% at 45.8% chord Max Cl/Cd 70.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe114-il) GOE 114 (MVA MK.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 114 (MVA MK.1) airfoil Max thickness 9.6% at 29.7% chord Max camber 3.5% at 49.7% chord Max Cl/Cd 70.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx79l100-il) FX 79-L-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 70.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(nplx-il) NPL AIRFOIL FROM ARC CP 1372		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL transonic airfoil FROM ARC CP 1372 Max thickness 10.7% at 35.8% chord Max camber 1.1% at 73.7% chord Max Cl/Cd 70.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database