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.

(goe244-il) GOE 244 (MVA PR.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 244 (MVA PR.4) airfoil Max thickness 17.7% at 19.6% chord Max camber 10% at 49.6% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe797-il) GOE 797 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 797 airfoil Max thickness 16% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah88k136-il) AH 88-K-136/16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe563-il) GOE 563 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 563 airfoil Max thickness 8.9% at 29.8% chord Max camber 2.2% at 49.8% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s4083-il) S4083 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe275-il) GOE 275 (DAIMLER VI) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 275 (DAIMLER VI) airfoil Max thickness 7.7% at 19.9% chord Max camber 4.7% at 29.9% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(curtisc72-il) Curtis C-72		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Curtis C-72 airfoil Max thickness 11.7% at 30% chord Max camber 3.8% at 50% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe366-il) GOE 366 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 366 airfoil Max thickness 13.1% at 29.8% chord Max camber 7.2% at 39.8% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe122-il) GOE 122 (MVA H.2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 122 (MVA H.2) airfoil Max thickness 7.3% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 73.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe796-il) GOE 796 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 796 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 73.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database