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.

(sd5060-il) SD5060 (9.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD5060 low Reynolds number airfoil Max thickness 9.5% at 24.9% chord Max camber 2% at 48.5% chord Max Cl/Cd 94.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe336-il) GOE 336 (MVA H.44) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 336 (MVA H.44) airfoil Max thickness 9% at 29.9% chord Max camber 5.4% at 29.9% chord Max Cl/Cd 94.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe626-il) GOE 626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 626 airfoil Max thickness 16.5% at 19.3% chord Max camber 5.1% at 49.3% chord Max Cl/Cd 94.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ma409-il) MA409 (original) (modified line 7)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Michael Achterberg MA409 F1C class free flight airfoil (original) Max thickness 6.8% at 25% chord Max camber 3.3% at 50% chord Max Cl/Cd 94.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s5010-il) S5010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S5010 low Reynolds number airfoil Max thickness 9.8% at 27.6% chord Max camber 1.8% at 32% chord Max Cl/Cd 94.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(mh110-il) MH 110 10.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord Max Cl/Cd 94.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(eh1590-il) EH 1.5/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.5/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1.5% at 25.9% chord Max Cl/Cd 94.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(vr13-il) BOEING-VERTOL VR-13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/Dadone VR-13 rotorcraft airfoil Max thickness 9.5% at 35% chord Max camber 2% at 20% chord Max Cl/Cd 94.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh62-il) MH 62 9.3%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 62 for flying wings Max thickness 9.3% at 26.9% chord Max camber 1.6% at 36.6% chord Max Cl/Cd 94.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh44-il) MH 44 9.66%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 44 for flying wings Max thickness 9.6% at 27.1% chord Max camber 1.5% at 36.9% chord Max Cl/Cd 94.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database