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.

(giiid-il) GIII BL86 AIRFOIL (modified line 31)		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 9.7% at 39.8% chord Max camber 1% at 29.8% chord Max Cl/Cd 70.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m5-il) NACA M5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-5 airfoil Max thickness 8.2% at 30.1% chord Max camber 2.1% at 30.1% chord Max Cl/Cd 70.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rhodesg36-il) Rhode St. Genese 36		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 36 airfoil Max thickness 16.2% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 70.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(c141f-il) LOCKHEED C-141 BL958.89 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 10% at 40.2% chord Max camber 2.3% at 45.1% chord Max Cl/Cd 70 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n5h10-il) NACA 5-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-10 rotorcraft airfoil Max thickness 9.9% at 40% chord Max camber 2.3% at 40% chord Max Cl/Cd 70 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(naca23018-il) NACA 23018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23018 airfoil Max thickness 18% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 70 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq158-il) HQ 1.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/8 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord Max Cl/Cd 70 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx60157-il) FX 60-157 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-157 airfoil Max thickness 15.7% at 40.2% chord Max camber 2.7% at 75% chord Max Cl/Cd 70 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rc410-il) NASA RC(4)-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC(4)-10 rotorcraft airfoil Max thickness 10% at 37.8% chord Max camber 2.1% at 30.3% chord Max Cl/Cd 69.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe435-il) GOE 435 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 435 airfoil Max thickness 26.1% at 27.8% chord Max camber 4.7% at 48% chord Max Cl/Cd 69.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database