Airfoil Tools
Search 1638 airfoils

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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.

(rc10b3-il) NASA/LANGLEY RC-10(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-10(B)3 rotorcraft airfoil Max thickness 10% at 37.7% chord Max camber 1.7% at 30.3% chord Source UIUC Airfoil Coordinates Database
(fx69h098-il) BELL/WORTMANN FX 69-H-098 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/Wortmann FX 69-H-098 rotorcraft airfoil Max thickness 9.9% at 28.2% chord Max camber 1.7% at 22.5% chord Source UIUC Airfoil Coordinates Database
(s4095-il) S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 9.7% at 29.1% chord Max camber 1.7% at 33.7% chord Source UIUC Airfoil Coordinates Database
(naca24112-jf) NACA 24112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord Source Javafoil generated
(raf69-il) RAF 69 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-69 airfoil Max thickness 20.6% at 30% chord Max camber 1.7% at 50% chord Source UIUC Airfoil Coordinates Database

(oa209-il) ONERA OA209 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 9% at 29.3% chord Max camber 1.6% at 17.1% chord Source UIUC Airfoil Coordinates Database
(e360-il) EPPLER 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E360 rotorcraft airfoil Max thickness 12.2% at 36.9% chord Max camber 1.6% at 27.2% chord Source UIUC Airfoil Coordinates Database
(mh62-il) MH 62 9.3%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 62 for flying wings Max thickness 9.3% at 26.9% chord Max camber 1.6% at 36.6% chord Source UIUC Airfoil Coordinates Database
(giiil-il) GIII BL387 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 35.1% chord Max camber 1.6% at 25.1% chord Source UIUC Airfoil Coordinates Database
(sc20706-il) NASA SC(2)-0706 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0706 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.6% at 82% chord Source UIUC Airfoil Coordinates Database