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.

(fx66h60-il) FX 66-H-60		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% 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
(mh30-il) MH 30 7.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 30 for F3E and F3B Max thickness 7.8% at 31% chord Max camber 1.7% at 46.4% chord Source UIUC Airfoil Coordinates Database
(mh43-il) MH 43 8.5%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 43 for F3B and F3E Max thickness 8.5% at 31.4% chord Max camber 1.7% at 36.4% chord Source UIUC Airfoil Coordinates Database
(mh45-il) MH 45 9.85%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 45 for flying wings Max thickness 9.8% at 26.9% chord Max camber 1.7% at 36.6% chord Source UIUC Airfoil Coordinates Database
(mh60-il) MH 60 10.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord Max camber 1.7% at 36.6% chord Source UIUC Airfoil Coordinates Database
(ms317-il) NASA/LANGLEY MS(1)-0317 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley MS(1)-0317 general aviation airfoil Max thickness 17% at 37.5% chord Max camber 1.7% at 72.5% 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
(naca632a015-il) NACA 63(2)A-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)A-015 airfoil Max thickness 15% at 37.1% chord Max camber 1.7% at 14.6% chord Source UIUC Airfoil Coordinates Database
(nlr7301-il) NLR-7301 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord Source UIUC Airfoil Coordinates Database

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