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.

(eh1590-il) EH 1.5/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.5/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1.5% at 25.9% chord Max Cl/Cd 80.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s8064-il) S8064		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF. Max thickness 12.3% at 37.8% chord Max camber 1.1% at 56.2% chord Max Cl/Cd 80.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe481a-il) GOE 481A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 481A airfoil Max thickness 15.3% at 29.4% chord Max camber 5.5% at 39.4% chord Max Cl/Cd 80.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe795-il) GOE 795 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 795 airfoil Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 80.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(arad20-il) ARA-D 20% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 20% thick propeller airfoil Max thickness 20% at 25% chord Max camber 3.8% at 25% chord Max Cl/Cd 80.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(c141c-il) LOCKHEED C-141 BL426.57 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 11% at 40.2% chord Max camber 1.3% at 50% chord Max Cl/Cd 80.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b707d-il) BOEING 707 .54 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 40% chord Max camber 1.8% at 30% chord Max Cl/Cd 80.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(isa961-il) I.S.A. 961		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 961 airfoil Max thickness 9.3% at 20% chord Max camber 4.6% at 40% chord Max Cl/Cd 80 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e502-il) EPPLER 502 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E502 general purpose airfoil Max thickness 15.6% at 42.1% chord Max camber 1.5% at 32.3% chord Max Cl/Cd 80 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ag13-il) AG13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG13 airfoil Max thickness 5.8% at 21.3% chord Max camber 2% at 41.8% chord Max Cl/Cd 79.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database