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.

(sc20010-il) NASA SC(2)-0010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(ea81006-il) EPPLER EA 8(-1)-006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 8(-1)-006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% 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
(ea61012-il) EPPLER EA 6(-1)-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(ah85l120-il) AH 85-L-120/17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

(ea61009-il) EPPLER EA 6(-1)-009 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-009 airfoil Max thickness 9% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(prandtl-d-tip-ns) Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider tip airfoil Max thickness 9.6% at 26.8% chord Max camber 0% at 0% chord Source NASA
(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(b540ols-il) BELL 540 AIRFOIL (MODIFIED NACA 0012)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell AH-1 rotor blade airfoil (operational loads survey) Max thickness 9.7% at 22.1% chord Max camber 0% at 0% 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