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.

(tempest3-il) HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 96.77% semispan airfoil (NPL?) Max thickness 10% at 38.7% chord Max camber 1% at 40.7% chord Source UIUC Airfoil Coordinates Database
(n6h10-il) NACA 6-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(naca64210-il) NACA 64-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(sd7032-il) SD7032-099-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord Source UIUC Airfoil Coordinates Database
(rae104-il) RAE 104 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

(naca66210-il) NACA 66-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(rae103-il) RAE 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(rc10n1-il) NASA/LANGLEY RC-10(N)1 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(N)1 rotorcraft airfoil Max thickness 10% at 37.6% chord Max camber 1.5% at 25% chord Source UIUC Airfoil Coordinates Database
(rae102-il) RAE 102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(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