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.

(mh83-il) MH 83 13.29%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 83 for flying wings (hang glider) Max thickness 13.3% at 20.6% chord Max camber 4.5% at 32.6% chord Max Cl/Cd 34.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e1233-il) EPPLER 1233 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord Max camber 4.4% at 29.8% chord Max Cl/Cd 34 at Re# 100,000 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 34 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ys915-il) YS-915		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	YS915 hydrofoil (Shen / Eppler) Max thickness 9.1% at 36.1% chord Max camber 1.8% at 65.6% chord Max Cl/Cd 34 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca634221-il) NACA 63(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 34 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(sc1012r8-il) SIKORSKY SC1012R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky SC1012 R8 rotorcraft airfoil Max thickness 12% at 27.8% chord Max camber 2.7% at 21.8% chord Max Cl/Cd 34 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(lwk80080-il) LWK 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-080 symmetrical airfoil Max thickness 8.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 33.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca22112-jf) NACA 22112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 22112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 0.8% at 9.6% chord Max Cl/Cd 33.9 at Re# 100,000 Source Javafoil generated
(e1211-il) EPPLER 1211 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1211 general aviation airfoil Max thickness 18% at 20.9% chord Max camber 4.4% at 37.7% chord Max Cl/Cd 33.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(joukowsk0009-jf) Joukovsky f=0% t=9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 9% symmetrical airfoil Max thickness 9% at 25.5% chord Max camber 0% at 0% chord Max Cl/Cd 33.9 at Re# 100,000 Source Javafoil generated