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.

(goe429-il) GOE 429 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 429 airfoil Max thickness 11.4% at 30% chord Max camber 0.2% at 10% chord Max Cl/Cd 58.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf30-il) RAF 30 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-30 airfoil Max thickness 12.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 58.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf27-il) RAF 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 58.4 at Re# 500,000 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 58.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ea61009-il) EPPLER EA 6(-1)-009 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-009 airfoil Max thickness 9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 58.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(mh26-il) MH 26 10.99%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 26 for F3D Pylon Racing (extended laminar flow) Max thickness 11% at 42.3% chord Max camber 1.4% at 42.3% chord Max Cl/Cd 58.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(cp-160-050-gn) Cambered plate C=16% T=5% R=0.86		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=16% Wall thickness=5% Radius=0.861 Max thickness 5.2% at 3.4% chord Max camber 14.3% at 49.2% chord Max Cl/Cd 58.3 at Re# 500,000 Source Generated
(naca63a210-il) NACA 63A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63A210 airfoil Max thickness 10% at 34.9% chord Max camber 1.3% at 50% chord Max Cl/Cd 58.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(bqm34-il) RYAN BQM-34 FIREBEE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Ryan BQM-34 Firebee wing airfoil (NACA 63-014A W/NACA 0014 nose and thinned to .09899 to account for sweep) Max thickness 9.9% at 32.5% chord Max camber 0% at 0% chord Max Cl/Cd 58.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe481-il) GOE 481 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 481 airfoil Max thickness 13.4% at 9.6% chord Max camber 8.8% at 39.4% chord Max Cl/Cd 58.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database