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.

(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord Max Cl/Cd 69.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe315-il) GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 315 (Hansa-Brandenburg III.5) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.1% at 29.9% chord Max Cl/Cd 69.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe284-il) GOE 284 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 284 airfoil Max thickness 17.7% at 29.3% chord Max camber 5.1% at 39.3% chord Max Cl/Cd 69.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ls413-il) NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0413 (GA(W)-2) general aviation airfoil Max thickness 12.9% at 37.5% chord Max camber 2.4% at 65% chord Max Cl/Cd 69.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx61184-il) FX 61-184 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-184 airfoil Max thickness 18.4% at 37.1% chord Max camber 3.1% at 62.9% chord Max Cl/Cd 69.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe527-il) GOE 527 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 527 airfoil Max thickness 16.5% at 29.5% chord Max camber 5.8% at 39.5% chord Max Cl/Cd 69.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf28-il) RAF 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-28 airfoil Max thickness 9.8% at 30% chord Max camber 1.9% at 40% chord Max Cl/Cd 69.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe288-il) GOE 288 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 288 airfoil Max thickness 17.4% at 29.3% chord Max camber 5.5% at 39.3% chord Max Cl/Cd 69.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd7080-il) SD7080 (9.2%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7080 low Reynolds number airfoil Max thickness 9.2% at 30% chord Max camber 2.1% at 44.4% chord Max Cl/Cd 69.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa27-il) USA 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27 airfoil Max thickness 11.1% at 30% chord Max camber 5.1% at 40% chord Max Cl/Cd 69.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database