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.

(sd8000-il) SD8000-089-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD8000 low Reynolds number airfoil Max thickness 8.9% at 29.4% chord Max camber 1.5% at 54% chord Source UIUC Airfoil Coordinates Database
(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord Max camber 4.3% at 30% chord Source UIUC Airfoil Coordinates Database
(s2050-il) S2050 8.93%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord Max camber 1.1% at 69.5% chord Source UIUC Airfoil Coordinates Database
(pw75-pw) PW75		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with some more reflex Max thickness 8.9% at 27.5% chord Max camber 1.5% at 23.4% chord Source RC Groups
(dh4009sm-il) dh4009sm		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft Max thickness 8.9% at 41.6% chord Max camber 0.2% at 9.6% chord Source UIUC Airfoil Coordinates Database

(pw51-pw) PW51		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord Max camber 1.4% at 27.5% chord Source RC Groups
(pw106-pw) PW106		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.9% at 27.5% chord Max camber 2.1% at 27.5% chord Source RC Groups
(goe164-il) GOE 164 (MVA MK.10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 164 (MVA MK.10) airfoil Max thickness 8.9% at 19.9% chord Max camber 6.6% at 39.9% chord Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Source UIUC Airfoil Coordinates Database
(e174-il) E174 (Dicke 8.92%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E174 low Reynolds number airfoil Max thickness 8.9% at 31.2% chord Max camber 3.3% at 44.9% chord Source UIUC Airfoil Coordinates Database