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.

(giiii-il) GIII BL288 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 40% chord Max camber 1.3% at 25% chord Max Cl/Cd 78 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20612-il) NASA SC(2)-0612 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0612 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.9% at 81% chord Max Cl/Cd 77.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe587-il) GOE 587 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 587 airfoil Max thickness 5.8% at 40% chord Max camber 3% at 30% chord Max Cl/Cd 77.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca0018-il) NACA 0018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 77.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca0015-il) NACA 0015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0015 airfoil Max thickness 15% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 77.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(vr1-il) BOEING-VERTOL VR-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-1 rotorcraft airfoil Max thickness 11% at 35.3% chord Max camber 1.5% at 43.3% chord Max Cl/Cd 77.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 77.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(c141b-il) LOCKHEED C-141 BL113.6 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 12.6% at 40.2% chord Max camber 1.1% at 64.5% chord Max Cl/Cd 77.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(b707e-il) BOEING 707 .99 SPAN 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 model 707 airfoils Max thickness 9% at 42% chord Max camber 1.8% at 34% chord Max Cl/Cd 77.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe09k-il) GOE 9K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord Max Cl/Cd 77.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database