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.

(bacnlf-il) BOEING HSNLF AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% 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
(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
(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
(tsagi8-il) TSAGI 8% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 8% airfoil Max thickness 8% at 30% chord Max camber 1.3% at 30% chord Source UIUC Airfoil Coordinates Database
(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
(s6063-il) S6063 7.05%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6063 low Reynolds number airfoil Max thickness 7% at 29.4% chord Max camber 1.3% at 43.8% chord Source UIUC Airfoil Coordinates Database
(rae69ck-il) RAE6-9CK AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Source UIUC Airfoil Coordinates Database
(vr8-il) BOEING-VERTOL VR-8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-8 rotorcraft airfoil Max thickness 8.2% at 35% chord Max camber 1.3% at 35% chord Source UIUC Airfoil Coordinates Database
(rae2822-il) RAE 2822 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Source UIUC Airfoil Coordinates Database

Page 134 of 164     124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143     Next

Please see the source web site or designer for any license conditions.