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.

(n0009sm-il) NACA-0009 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n11h9-il) NACA 11-H-09 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 11-H-9 rotorcraft airfoil Max thickness 9% at 40.2% chord Max camber 4.5% at 30% chord Source UIUC Airfoil Coordinates Database
(n6409-il) NACA6409 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord Source UIUC Airfoil Coordinates Database
(naca16009-il) NACA 16009		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca63209-il) NACA 63-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64209-il) NACA 64-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca66209-il) NACA 66-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% 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
(rg12a-il) AIRFOIL PROFILE12A 9.00%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12A airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord Source UIUC Airfoil Coordinates Database

Page 43 of 164     33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52     Next

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