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.

(naca652415-il) NACA 65(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 23.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cp-100-050-gn) Cambered plate C=10% T=5% R=1.3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=10% Wall thickness=5% Radius=1.3 Max thickness 7% at 4.2% chord Max camber 7.9% at 46.5% chord Max Cl/Cd 23.9 at Re# 50,000 Source Generated
(mrc-20-il) MRC-20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela MRC-20 Max thickness 15.6% at 38.2% chord Max camber 2.9% at 48% chord Max Cl/Cd 23.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe413-il) GOE 413 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 413 airfoil Max thickness 16.4% at 30% chord Max camber 4.6% at 40% chord Max Cl/Cd 23.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah88k130-il) AH 88-K-130/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-130/20 airfoil for use with flaps (K) Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord Max Cl/Cd 23.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(s9027-il) S9027 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord Max Cl/Cd 23.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx77080-il) WORTMANN FX 77-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-080 symmetrical airfoil Max thickness 8% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 23.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D root (BL17.5) airfoil Max thickness 16.5% at 38.9% chord Max camber 1.3% at 68.3% chord Max Cl/Cd 23.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca22112-jf) NACA 22112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 22112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 0.8% at 9.6% chord Max Cl/Cd 23.9 at Re# 50,000 Source Javafoil generated
(vr9-il) BOEING-VERTOL VR-9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-9 rotorcraft airfoil Max thickness 6.1% at 35% chord Max camber 0.3% at 35% chord Max Cl/Cd 23.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database