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.

(sc20518-il) NASA SC(2)-0518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord Max Cl/Cd 26 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe632-il) GOE 632 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 632 airfoil Max thickness 14% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 26 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq09-il) HQ 0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 26 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh114-il) MH 114 13.02%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 114 for a propeller for ultralight Max thickness 13% at 28.1% chord Max camber 6.4% at 50% chord Max Cl/Cd 26 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e428-il) EPPLER 428 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E428 airfoil Max thickness 11.1% at 17.2% chord Max camber 0.5% at 50.6% chord Max Cl/Cd 26 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe704-il) GOE 704 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 704 airfoil Max thickness 12.9% at 29.9% chord Max camber 2.1% at 39.9% chord Max Cl/Cd 26 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx63137sm-il) FX 63-137 13.7% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-137 airfoil (smoothed) Max thickness 13.7% at 30.9% chord Max camber 5.8% at 56.5% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca001234-il) NACA 0012-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-34 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ames01-il) NASA/AMES A-01 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database