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.

(giiim-il) GIII BL430 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.2% chord Max camber 1.9% at 25.2% chord Max Cl/Cd 31.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe81-il) GOE 81 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 81 airfoil Max thickness 7.4% at 29.9% chord Max camber 6.3% at 29.9% chord Max Cl/Cd 31.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe611-il) GOE 611 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 611 airfoil Max thickness 12.9% at 29.9% chord Max camber 5.8% at 39.9% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rc08b3-il) NASA/LANGLEY RC-08(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(B)3 rotorcraft airfoil Max thickness 8% at 37.8% chord Max camber 1.1% at 34.1% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx69h098-il) BELL/WORTMANN FX 69-H-098 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/Wortmann FX 69-H-098 rotorcraft airfoil Max thickness 9.9% at 28.2% chord Max camber 1.7% at 22.5% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(mrc-16-il) MRC-16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela MRC-16 Max thickness 13.9% at 34.6% chord Max camber 3% at 40.3% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c141c-il) LOCKHEED C-141 BL426.57 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 11% at 40.2% chord Max camber 1.3% at 50% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e203-il) E203 (13.64%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E203 low Reynolds number airfoil Max thickness 13.6% at 30.7% chord Max camber 2.3% at 54.1% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(bacxxx-il) BOEING BACXXX AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx38153-il) FX 38-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord Max Cl/Cd 31.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database