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.

(naca1410-il) NACA 1410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1410 airfoil Max thickness 10% at 29.9% chord Max camber 1% at 50% chord Max Cl/Cd 42.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca651212-il) NACA 65(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 42.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh108-il) MH 108 11.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 108 for stall controlled wind turbines Max thickness 11.9% at 22.8% chord Max camber 1% at 22.8% chord Max Cl/Cd 42.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe681-il) GOE 681 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 681 airfoil Max thickness 16.8% at 29.2% chord Max camber 4.4% at 39.2% chord Max Cl/Cd 42.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(npl9626-il) NPL 9626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9626 rotorcraft airfoil Max thickness 12.1% at 30.9% chord Max camber 0.7% at 30.9% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(usa49-il) USA 49 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-49 airfoil Max thickness 7.3% at 30% chord Max camber 1.7% at 30% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fxl142k-il) FX LIII-142 K 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX LIII-142 K 25 airfoil Max thickness 14.2% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe502-il) GOE 502 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 502 airfoil Max thickness 15.9% at 29.3% chord Max camber 6.1% at 49.4% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(stcyr234-il) St. CYR 234 (Bartel 17-IC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 234 (Bartel 17-IC) airfoil Max thickness 16% at 20% chord Max camber 5.1% at 50% chord Max Cl/Cd 42.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database