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.

(k2-il) GRUMMAN K-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-2 transonic airfoil (GAC .80-.53-10.3) Max thickness 10.3% at 38.9% chord Max camber 1.3% at 88.3% chord Source UIUC Airfoil Coordinates Database
(kc135a-il) KC-135 BL52.44 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord Max camber 1.3% at 20% chord Source UIUC Airfoil Coordinates Database
(mh94-il) MH 94 16.03%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Source UIUC Airfoil Coordinates Database
(naca001034a08cli02-il) NACA 0010-34 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-34 a=0.8 c(li)=0.2 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca63a210-il) NACA 63A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63A210 airfoil Max thickness 10% at 34.9% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64a210-il) NACA 64A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(nl722343-il) NLR-7223-43 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-43 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 74% chord Source UIUC Airfoil Coordinates Database
(nl722362-il) NLR-7223-62 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 21.6% chord Source UIUC Airfoil Coordinates Database
(nlr1t-il) NLR-1T AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord Max camber 1.3% at 22.3% chord Source UIUC Airfoil Coordinates Database
(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D root (BL17.5) airfoil Max thickness 16.5% at 38.9% chord Max camber 1.3% at 68.3% chord Source UIUC Airfoil Coordinates Database

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