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.

(goe277-il) GOE 277 (DAIMLER VIII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 277 (DAIMLER VIII) airfoil Max thickness 8.3% at 29.9% chord Max camber 4.4% at 29.9% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx66s161-il) FX 66-S-161 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-161 airfoil Max thickness 16.1% at 33.9% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe507-il) GOE 507 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e562-il) EPPLER 562 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E562 general aviation airfoil Max thickness 15% at 27.6% chord Max camber 4% at 50.8% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx74cl5140-il) FX74_CL5_140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe533-il) GOE 533 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 533 airfoil Max thickness 13.7% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq3013-il) HQ 3.0/13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/13 R/C sailplane airfoil Max thickness 13% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 73.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe701-il) GOE 701 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 701 airfoil Max thickness 12.5% at 29.6% chord Max camber 4.9% at 39.6% chord Max Cl/Cd 73.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr7-il) BOEING-VERTOL VR-7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-7 rotorcraft airfoil Max thickness 12% at 33% chord Max camber 3.1% at 33% chord Max Cl/Cd 73.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database