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.

(e385-il) E385 (8.41%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E385 airfoil Max thickness 8.4% at 29.6% chord Max camber 5.3% at 47.5% chord Max Cl/Cd 139 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e471-il) E471 (6.25%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E471 airfoil Max thickness 6.3% at 29.8% chord Max camber 4.5% at 53.5% chord Max Cl/Cd 138.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx76mp140-il) FX 76-MP-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-140 airfoil Max thickness 14.1% at 33.9% chord Max camber 7.1% at 46.7% chord Max Cl/Cd 138.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh122-il) MH 122 9.32%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 122 for tip section of a propeller Max thickness 9.3% at 37.6% chord Max camber 3.4% at 64.3% chord Max Cl/Cd 137.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah79100c-il) AH 79-100 C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100C airfoil Max thickness 9.9% at 30.9% chord Max camber 6.7% at 50% chord Max Cl/Cd 137.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(e216-il) E216 (10.4%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E216 low Reynolds number airfoil Max thickness 10.4% at 26.2% chord Max camber 4.7% at 59% chord Max Cl/Cd 136.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(dae21-il) DAE-21 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE21 low Reynolds number airfoil Max thickness 11.8% at 32% chord Max camber 6.6% at 43.7% chord Max Cl/Cd 136.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e395-il) EPPLER 395 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E395 human e664ered aircraft airfoil Max thickness 12.3% at 29.5% chord Max camber 5.2% at 52.3% chord Max Cl/Cd 136.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(dae11-il) DAE-11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord Max camber 6.6% at 44.4% chord Max Cl/Cd 135.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e397-il) EPPLER 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E397 human powered aircraft airfoil Max thickness 13.5% at 29.4% chord Max camber 5.3% at 52.1% chord Max Cl/Cd 135.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database