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.

(hq3012-il) HQ 3.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3% at 50% chord Source UIUC Airfoil Coordinates Database
(hq3512-il) HQ 3.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3.5% at 50% chord Source UIUC Airfoil Coordinates Database
(hs1712-il) HAM-STD HS1-712 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 12% at 36% chord Max camber 4.9% at 44% chord Source UIUC Airfoil Coordinates Database
(j5012-il) J5012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Jef Raskin (originator of the Apple Macintosh Project) J5012 airfoil Max thickness 12% at 34.5% chord Max camber 0% at 83.5% chord Source UIUC Airfoil Coordinates Database
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord Source UIUC Airfoil Coordinates Database
(lds2-il) LDS-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord Source UIUC Airfoil Coordinates Database
(m15-il) NACA M15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% chord Source UIUC Airfoil Coordinates Database
(m18-il) NACA M18 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database
(m21-il) NACA M21 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-21 airfoil Max thickness 12% at 30% chord Max camber 6% at 30% chord Source UIUC Airfoil Coordinates Database
(m24-il) NACA M24 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-24 airfoil Max thickness 12% at 30.1% chord Max camber 6.3% at 30.1% chord Source UIUC Airfoil Coordinates Database

Page 85 of 164     75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94     Next

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