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.

(ag10-il) AG10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG10 airfoil Max thickness 4.7% at 16% chord Max camber 1.7% at 32.1% chord Max Cl/Cd 41.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(pw51-pw) PW51		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord Max camber 1.4% at 27.5% chord Max Cl/Cd 41.2 at Re# 100,000 Source RC Groups
(e520-il) EPPLER 520 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E520 tailplane airfoil Max thickness 15% at 36.7% chord Max camber 0% at 0% chord Max Cl/Cd 41.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(v23010-il) BOEING-VERTOL V23010-1.58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V23010-1.58 rotorcraft airfoil Max thickness 10.2% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 41.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(as5048-il) AS5048 (18%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil Max thickness 18% at 38.3% chord Max camber 0.8% at 77.8% chord Max Cl/Cd 41.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e874-il) EPPLER 874 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E874 hydrofoil Max thickness 7.9% at 28.8% chord Max camber 0.9% at 35.7% chord Max Cl/Cd 41.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe367-il) GOE 367 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 367 airfoil Max thickness 16.3% at 29.7% chord Max camber 4.6% at 39.7% chord Max Cl/Cd 41.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e558-il) EPPLER 558 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E558 general aviation airfoil Max thickness 16% at 26.4% chord Max camber 3.8% at 49.3% chord Max Cl/Cd 41.2 at Re# 100,000 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 41.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ls417mod-il) NASA/LANGLEY LS(1)-0417MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0417MOD general aviation airfoil Max thickness 17% at 30.2% chord Max camber 2.3% at 20.2% chord Max Cl/Cd 41.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database