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.

(goe803h-il) GOE 803 (HACKLINGER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 803 (Hacklinger) airfoil Max thickness 6.3% at 15% chord Max camber 6.6% at 40% chord Max Cl/Cd 128.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx73cl3152-il) FX 73-CL3-152		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-CL3-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 8% at 43.5% chord Max Cl/Cd 128.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe492-il) GOE 492 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 492 airfoil Max thickness 6.2% at 29.9% chord Max camber 3.4% at 49.9% chord Max Cl/Cd 128.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m23-il) NACA M23 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-23 airfoil Max thickness 8.1% at 30.1% chord Max camber 6.4% at 30.1% chord Max Cl/Cd 128.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e174-il) E174 (Dicke 8.92%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E174 low Reynolds number airfoil Max thickness 8.9% at 31.2% chord Max camber 3.3% at 44.9% chord Max Cl/Cd 128.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe366-il) GOE 366 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 366 airfoil Max thickness 13.1% at 29.8% chord Max camber 7.2% at 39.8% chord Max Cl/Cd 128.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sd7034-il) SD7034		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7034 low Reynolds number airfoil Max thickness 10.5% at 26% chord Max camber 3.6% at 39.4% chord Max Cl/Cd 128.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n8h12-il) NACA 8-H-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord Max Cl/Cd 128.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m21-il) NACA M21 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-21 airfoil Max thickness 12% at 30% chord Max camber 6% at 30% chord Max Cl/Cd 128.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe63-il) GOE 63 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 63 airfoil Max thickness 8.3% at 19.9% chord Max camber 6.7% at 39.9% chord Max Cl/Cd 128.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database