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.

(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Modified Naca 0012 airfoil for Sandia VAWT tests Max thickness 12.2% at 22.5% chord Max camber 0% at 0% chord Max Cl/Cd 20.3 at Re# 50,000 Source Sandia National Laboratories
(ah82150a-il) AH 82-150 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord Max Cl/Cd 20.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca747a315-il) NACA 747A315		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A315 airfoil Max thickness 15% at 40.2% chord Max camber 2.5% at 35% chord Max Cl/Cd 20.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe431-il) GOE 431 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 431 airfoil Max thickness 11.8% at 20% chord Max camber 7.2% at 60% chord Max Cl/Cd 20.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e475-il) E475 (15.01%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E475 aerobatic aircraft airfoil Max thickness 15% at 21.7% chord Max camber 0% at 0% chord Max Cl/Cd 20.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(lrn1015-il) NASA LRN 1015 (NASA TM 102840)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil Max thickness 15.2% at 40% chord Max camber 4.9% at 44% chord Max Cl/Cd 20.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11		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=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord Max camber 2.7% at 52.1% chord Max Cl/Cd 20.1 at Re# 50,000 Source Generated
(e540-il) EPPLER 540 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E540 general aviation airfoil Max thickness 16.9% at 45.5% chord Max camber 1.6% at 35.7% chord Max Cl/Cd 20.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe09k-il) GOE 9K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord Max Cl/Cd 20.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ht08-il) HT08		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT08 airfoil Max thickness 5% at 20.2% chord Max camber 0% at 0% chord Max Cl/Cd 20.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database