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.

(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley Whitcomb integral supercritical airfoil Max thickness 11% at 35% chord Max camber 2.4% at 82.5% chord Max Cl/Cd 27.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe10k-il) GOE 10K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 10K airfoil Max thickness 3.9% at 50% chord Max camber 1.4% at 60% chord Max Cl/Cd 27.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx78k140a20-il) FX 78-K-140 A/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-K-140 airfoil for use with flaps (K) A/20 Max thickness 14.1% at 43.5% chord Max camber 4.4% at 43.5% chord Max Cl/Cd 27.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e421-il) EPPLER 421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E421 high lift airfoil Max thickness 14.5% at 26% chord Max camber 8.6% at 37.4% chord Max Cl/Cd 27.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m2-il) NACA M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-2 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(fx05191-il) WORTMANN FX 05-191 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-191 airfoil Max thickness 19.1% at 37.1% chord Max camber 2.6% at 50% chord Max Cl/Cd 27.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m1-il) NACA-M1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-1 airfoil Max thickness 6.2% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(dh4009sm-il) dh4009sm		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft Max thickness 8.9% at 41.6% chord Max camber 0.2% at 9.6% chord Max Cl/Cd 27.6 at Re# 100,000 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 27.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fxs03182-il) FX S 03-182 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 03-182 airfoil Max thickness 18.2% at 40.2% chord Max camber 2.9% at 56.5% chord Max Cl/Cd 27.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database