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.

(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0013 general aviation airfoil Max thickness 12.9% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 39.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe05k-il) GOE 5K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 5K airfoil Max thickness 3.7% at 50% chord Max camber 1.5% at 50% chord Max Cl/Cd 39.8 at Re# 200,000 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 39.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s9033-il) S9033 (7.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord Max Cl/Cd 39.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e297-il) EPPLER 297 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E297 tailplane airfoil Max thickness 11.4% at 37.7% chord Max camber 0% at 0% chord Max Cl/Cd 39.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(marske4-il) MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID tip airfoil (NACA 43012A*.833 hybrid) Max thickness 10.2% at 20% chord Max camber 2.8% at 15% chord Max Cl/Cd 39.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20010-il) NASA SC(2)-0010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 39.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca16009-il) NACA 16009		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 39.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe460-il) GOE 460 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 460 airfoil Max thickness 20.5% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 39.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx77w270-il) FX 77-W-270		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-270 airfoil for use on wind turbines (W) Max thickness 27.1% at 33.9% chord Max camber 4.3% at 27.9% chord Max Cl/Cd 39.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database