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.

(m23-il) NACA M23 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-23 airfoil Max thickness 8.1% at 30.1% chord Max camber 6.4% at 30.1% 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
(m25-il) NACA M25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord Max camber 8.2% at 30% chord Source UIUC Airfoil Coordinates Database
(m26-il) NACA M26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-26 airfoil Max thickness 8.3% at 40% chord Max camber 8.3% at 30% chord Source UIUC Airfoil Coordinates Database
(m27-il) NACA M27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-27 airfoil Max thickness 12% at 30.1% chord Max camber 8.4% at 30.1% chord Source UIUC Airfoil Coordinates Database

(m3-il) NACA M3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(m4-il) NACA M4 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-4 airfoil Max thickness 6.3% at 30% chord Max camber 2.2% at 30% chord Source UIUC Airfoil Coordinates Database
(m5-il) NACA M5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-5 airfoil Max thickness 8.2% at 30.1% chord Max camber 2.1% at 30.1% chord Source UIUC Airfoil Coordinates Database
(m6-il) NACA M6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Source UIUC Airfoil Coordinates Database
(m665-il) M6 (65%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M6 (65%) Max thickness 7.8% at 30% chord Max camber 1.4% at 30% chord Source UIUC Airfoil Coordinates Database