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.

(fx6617ai-il) WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17AII-182 airfoil (as tested at NASA) Max thickness 18.8% at 35.3% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 105.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m27-il) NACA M27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-27 airfoil Max thickness 12% at 30.1% chord Max camber 8.4% at 30.1% chord Max Cl/Cd 105.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah83159-il) AH 83-159		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord Max Cl/Cd 105.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe612-il) GOE 612 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 612 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord Max Cl/Cd 105.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe553-il) GOE 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 553 airfoil Max thickness 13.7% at 29.6% chord Max camber 4.7% at 39.6% chord Max Cl/Cd 105.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe621-il) GOE 621 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 621 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord Max Cl/Cd 105.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah93k131-il) AH 93-K-131/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-131/15 airfoil for use with flaps (K) Max thickness 13.1% at 41.3% chord Max camber 3.6% at 41.3% chord Max Cl/Cd 105.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd7032-il) SD7032-099-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord Max Cl/Cd 105.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe402-il) GOE 402 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 402 airfoil Max thickness 6.8% at 20% chord Max camber 5.7% at 30% chord Max Cl/Cd 105.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(gs1-il) SIKORSKY GS-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gluharoff/Sikorsky GS-1 airfoil Max thickness 13.9% at 30% chord Max camber 4.1% at 50% chord Max Cl/Cd 105.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database