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.

(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 28.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe776-il) GOE 776 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 776 airfoil Max thickness 25% at 30% chord Max camber 0% at 60% chord Max Cl/Cd 28.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ht08-il) HT08		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT08 airfoil Max thickness 5% at 20.2% chord Max camber 0% at 0% chord Max Cl/Cd 28.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca16018-il) NACA 16-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-018 airfoil Max thickness 18% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 28.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca644221-il) NACA 64(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 28.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(hs1430-il) HAM-STD HS1-430 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 30% at 34% chord Max camber 3% at 44% chord Max Cl/Cd 28.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx75vg166-il) FX 75-VG-166/22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 75-VG-166/22 variable geometry airfoil Max thickness 16.7% at 43.5% chord Max camber 2.4% at 40.2% chord Max Cl/Cd 28.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e341-il) EPPLER 341 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E341 flying wing airfoil Max thickness 13.9% at 32.8% chord Max camber 3% at 23.2% chord Max Cl/Cd 28.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc20010-il) NASA SC(2)-0010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 28.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nlf415-il) NASA/LANGLEY NLF(2)-0415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil Max thickness 15% at 47.1% chord Max camber 3% at 71.4% chord Max Cl/Cd 28.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database