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.

(hobie-il) HOBIE		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.5% at 25% chord Max camber 4% at 45% chord Max Cl/Cd 76.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe364-il) GOE 364 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 364 airfoil Max thickness 10.8% at 30% chord Max camber 6.5% at 30% chord Max Cl/Cd 76.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e855-il) EPPLER 855 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E855 propeller airfoil Max thickness 15.7% at 32.2% chord Max camber 3.7% at 50.6% chord Max Cl/Cd 76.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx74modsm-il) FX 74-Cl5-140 MOD (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Modified Wortmann FX 74-CL5-140 high lift airfoil Max thickness 13.1% at 27.1% chord Max camber 9.7% at 41.6% chord Max Cl/Cd 76.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s2091-il) S2091-101-83		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2091 low Reynolds number airfoil Max thickness 10.1% at 26% chord Max camber 3.7% at 39.5% chord Max Cl/Cd 76.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(mh120-il) MH 120 11.57%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 120 for tip section of a propeller Max thickness 11.6% at 34.7% chord Max camber 2.2% at 44.2% chord Max Cl/Cd 76.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord Max Cl/Cd 76.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(curtisc72-il) Curtis C-72		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Curtis C-72 airfoil Max thickness 11.7% at 30% chord Max camber 3.8% at 50% chord Max Cl/Cd 76.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s1221-flap-il) S1221 w/ 4 deg flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord Max Cl/Cd 76.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx76mp160-il) FX 76-MP-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-160 airfoil Max thickness 16.1% at 33.9% chord Max camber 6.1% at 50% chord Max Cl/Cd 76.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database