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.

(hq309-il) HQ 3.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3% at 50% chord Source UIUC Airfoil Coordinates Database
(hs1430-il) HAM-STD HS1-430 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 30% at 34% chord Max camber 3% at 44% chord Source UIUC Airfoil Coordinates Database
(marske1-il) MARSKE XM-1D AIRFOIL (F14-3.0)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske XM-1D airfoil (F14-3.0) Max thickness 14% at 25.1% chord Max camber 3% at 25.1% chord Source UIUC Airfoil Coordinates Database
(mh121-il) MH 121 8.76%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 121 for tip section of a propeller Max thickness 8.8% at 37.9% chord Max camber 3% at 62.2% chord Source UIUC Airfoil Coordinates Database
(mh70-il) MH 70 11.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 70 for fying wing (full size) Max thickness 11.1% at 29.4% chord Max camber 3% at 39.6% chord Source UIUC Airfoil Coordinates Database

(mrc-16-il) MRC-16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela MRC-16 Max thickness 13.9% at 34.6% chord Max camber 3% at 40.3% chord Source UIUC Airfoil Coordinates Database
(naca652415a05-il) NACA 65(2)-415 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-415 a=0.5 airfoil Max thickness 15% at 39.9% chord Max camber 3% at 45% chord Source UIUC Airfoil Coordinates Database
(naca654421a05-il) NACA 65(4)-421 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 a=0.5 airfoil Max thickness 21% at 39.9% chord Max camber 3% at 45% chord Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Source UIUC Airfoil Coordinates Database
(nlf415-il) NASA/LANGLEY NLF(2)-0415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil Max thickness 15% at 47.1% chord Max camber 3% at 71.4% chord Source UIUC Airfoil Coordinates Database