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.

(goe798-il) GOE 798 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 798 airfoil Max thickness 20% at 30% chord Max camber 6% at 40% chord Max Cl/Cd 84.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca23018-il) NACA 23018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23018 airfoil Max thickness 18% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 84.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe12k-il) GOE 12K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 12K airfoil Max thickness 11.1% at 50% chord Max camber 4.1% at 60% chord Max Cl/Cd 84.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca63209-il) NACA 63-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 84.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq208-il) HQ 2.0/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 84.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(mh30-il) MH 30 7.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 30 for F3E and F3B Max thickness 7.8% at 31% chord Max camber 1.7% at 46.4% chord Max Cl/Cd 84.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 84.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx83w227-il) FX 83-W-227		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 83-W-227 airfoil for use on wind turbines (W) Max thickness 22.6% at 33.9% chord Max camber 3.4% at 40.2% chord Max Cl/Cd 84.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(joukowsk0021-jf) Joukovsky f=0% t=21%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 21% symmetrical airfoil Max thickness 21% at 26.6% chord Max camber 0% at 0% chord Max Cl/Cd 84.3 at Re# 1,000,000 Source Javafoil generated
(naca671215-il) NACA 67		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 67 Max thickness 15% at 50% chord Max camber 1.1% at 50% chord Max Cl/Cd 84.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database