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.

(goe374-il) GOE 374 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 374 airfoil Max thickness 6.5% at 30% chord Max camber 4.5% at 30% chord Max Cl/Cd 32.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e378-il) EPPLER 378 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E378 ultralight airfoil Max thickness 4.1% at 7.8% chord Max camber 8.1% at 35.9% chord Max Cl/Cd 32.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(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 32.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(boe103-il) BOEING 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 103 airfoil Max thickness 12.7% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 32.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s8066-il) S8066 (10% version of S8065 w/ lower surface aerodynamically similar)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-40 pylon racing (10%). Max thickness 10% at 37.7% chord Max camber 0.8% at 56.3% chord Max Cl/Cd 32.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(apex16-il) Apex 16 (normalized using XFOIL date021206)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela Apex 16 low Reynolds number transonic research airfoil Max thickness 12.9% at 38.6% chord Max camber 2.4% at 59.6% chord Max Cl/Cd 32.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s3014-il) S3014-095-85		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3014 low Reynolds number airfoil Max thickness 9.5% at 29.4% chord Max camber 2.6% at 38.6% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(raf15-il) RAF 15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-15 airfoil Max thickness 6.5% at 15% chord Max camber 2.6% at 30% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe326-il) GOE 326 (PFALZ 55) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 326 (Pfalz 55) airfoil Max thickness 8.2% at 29.9% chord Max camber 4.7% at 39.9% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe344-il) GOE 344 (PFALZ 71) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord Max Cl/Cd 32.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database