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.

(giiig-il) GIII BL167 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 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 62.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(r140sm-il) R140 12.04% (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	R140 Quickee 500 airfoil (smoothed) Max thickness 12% at 39.3% chord Max camber 0.4% at 39.3% chord Max Cl/Cd 62 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd8020-il) SD8020-010-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD8020 low Reynolds number airfoil Max thickness 10.1% at 27.5% chord Max camber 0% at 42.1% chord Max Cl/Cd 62 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b707c-il) BOEING 707 .40 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 9.6% at 30% chord Max camber 1.9% at 15% chord Max Cl/Cd 61.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe506-il) GOE 506 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 506 airfoil Max thickness 16.5% at 29.3% chord Max camber 4.7% at 39.3% chord Max Cl/Cd 61.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(naca66210-il) NACA 66-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 61.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m665-il) M6 (65%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M6 (65%) Max thickness 7.8% at 30% chord Max camber 1.4% at 30% chord Max Cl/Cd 61.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiib-il) GIII BL45 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 10.4% at 39.7% chord Max camber 0.8% at 24.7% chord Max Cl/Cd 61.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe518-il) GOE 518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 518 airfoil Max thickness 18% at 29.8% chord Max camber 7.3% at 29.8% chord Max Cl/Cd 61.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n0012-il) NACA 0012 AIRFOILS		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 61.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database