Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(goe683-il) GOE 683 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 683 airfoil Max thickness 19.9% at 30% chord Max camber 3% at 30% chord Max Cl/Cd 31.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(vr9-il) BOEING-VERTOL VR-9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-9 rotorcraft airfoil Max thickness 6.1% at 35% chord Max camber 0.3% at 35% chord Max Cl/Cd 31.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ames02-il) NASA/AMES A-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-02 transonic rotorcraft airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord Max Cl/Cd 31.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(a63a108c-il) NASA/AMES 63A108 MOD C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES modification of the NACA 63A-108 airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord Max Cl/Cd 31.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(b707b-il) BOEING 707 .19 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 12.1% at 29.9% chord Max camber 0.7% at 9.9% chord Max Cl/Cd 31.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e552-il) EPPLER 552 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E552 general aviation airfoil Max thickness 18.4% at 32.4% chord Max camber 2.6% at 51.8% chord Max Cl/Cd 31.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s1012-il) S1012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord Max camber 0% at 0% chord Max Cl/Cd 31.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord Max Cl/Cd 31.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(raf30md-il) RAF 30 MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-30 MOD airfoil Max thickness 7.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 31 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc20714-il) NASA SC(2)-0714 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (NASA TP-2969) Max thickness 14% at 37% chord Max camber 2.5% at 81% chord Max Cl/Cd 31 at Re# 100,000 Source UIUC Airfoil Coordinates Database