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.

(goe07k-il) GOE 7K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 7K airfoil Max thickness 11% at 50% chord Max camber 4.5% at 50% chord Max Cl/Cd 38.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah88k136-il) AH 88-K-136/16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord Max Cl/Cd 38.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(vr8-il) BOEING-VERTOL VR-8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-8 rotorcraft airfoil Max thickness 8.2% at 35% chord Max camber 1.3% at 35% chord Max Cl/Cd 38.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s8035-il) S8035 for RC aerobatic 14% thick		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8035 low Reynolds number airfoil Max thickness 14% at 29.1% chord Max camber 0% at 0% chord Max Cl/Cd 38.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(amsoil2-il) RUTAN WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer wing airfoil Max thickness 11.8% at 39% chord Max camber 1% at 48% chord Max Cl/Cd 38.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e228-il) E10(08%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E228 low Reynolds number airfoil Max thickness 10.1% at 31.9% chord Max camber 0.3% at 31.9% chord Max Cl/Cd 38.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(us1000root-il) US1000ROOT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord Max camber 0% at 0% chord Max Cl/Cd 38.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nlf1015-il) NASA NLF1015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil Max thickness 15% at 39.8% chord Max camber 4.3% at 62.8% chord Max Cl/Cd 38.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx79l100-il) FX 79-L-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 38.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe289-il) GOE 289 (MVA 289) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 289 (MVA 289) airfoil Max thickness 16.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 38.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database