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.

(tsagi8-il) TSAGI 8% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 8% airfoil Max thickness 8% at 30% chord Max camber 1.3% at 30% chord Max Cl/Cd 57.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s102b-il) SOMERS S102 AIRFOIL (BLUNT)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2% at 68.7% chord Max Cl/Cd 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe511-il) GOE 511 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 511 airfoil Max thickness 16.6% at 19.9% chord Max camber 8% at 29.8% chord Max Cl/Cd 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e1212mod-il) EPPLER E1212MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1212 general aviation airfoil (as modified for use as Quickie wing airfoil) Max thickness 17.7% at 20.1% chord Max camber 2.6% at 35.1% chord Max Cl/Cd 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe575-il) GOE 575 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord Max Cl/Cd 57.6 at Re# 200,000 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 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe235-il) GOE 235 (SCHTTE-LANZ) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 235 (SCHATTE-LANZ) airfoil Max thickness 6.5% at 19.9% chord Max camber 3.5% at 39.9% chord Max Cl/Cd 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah93w215-il) AH 93-W-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-215 airfoil for use on wind turbines (W) Max thickness 21.2% at 33.9% chord Max camber 3.1% at 40.2% chord Max Cl/Cd 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca1412-il) NACA 1412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord Max Cl/Cd 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe648-il) GOE 648 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 648 airfoil Max thickness 15.2% at 29.4% chord Max camber 3.9% at 39.4% chord Max Cl/Cd 57.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database