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.

(goe226-il) GOE 226 (MVA H.36) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 226 (MVA H.36) airfoil Max thickness 13.9% at 19.7% chord Max camber 8.1% at 49.7% chord Max Cl/Cd 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe459-il) GOE 459 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 459 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh115-il) MH 115 11.06%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 115 for a propeller for ultralight Max thickness 11.1% at 29.8% chord Max camber 5.5% at 46% chord Max Cl/Cd 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe513-il) GOE 513 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 513 airfoil Max thickness 16.6% at 29.8% chord Max camber 5.2% at 39.8% chord Max Cl/Cd 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(supermarine371i-il) Supermarine 371-I (root)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord Max Cl/Cd 28.6 at Re# 50,000 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 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca25112-jf) NACA 25112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 25112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 2% at 27.2% chord Max Cl/Cd 28.6 at Re# 50,000 Source Javafoil generated
(giiin-il) GIII BL450 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 8.4% at 30.2% chord Max camber 2.1% at 20.2% chord Max Cl/Cd 28.6 at Re# 50,000 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 28.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database