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.

(goe358-il) GOE 358 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 358 airfoil Max thickness 10.9% at 20% chord Max camber 5.6% at 50% chord Max Cl/Cd 61.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah79100c-il) AH 79-100 C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100C airfoil Max thickness 9.9% at 30.9% chord Max camber 6.7% at 50% chord Max Cl/Cd 61.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq3510-il) HQ 3.5/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 61.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe118-il) GOE 118 (MVA MK.7) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 118 (MVA MK.7) airfoil Max thickness 8.6% at 29.9% chord Max camber 5.7% at 39.9% chord Max Cl/Cd 61.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe81-il) GOE 81 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 81 airfoil Max thickness 7.4% at 29.9% chord Max camber 6.3% at 29.9% chord Max Cl/Cd 61.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(s4320-il) S4320		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4320 low Reynolds number airfoil Max thickness 9.4% at 26.8% chord Max camber 4.5% at 40.2% chord Max Cl/Cd 61.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh38-il) MH 38 9.68%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 38 for Endurance Model Max thickness 9.7% at 31.6% chord Max camber 3.9% at 45.3% chord Max Cl/Cd 61.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n6409-il) NACA6409 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord Max Cl/Cd 61.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e377m-il) EPPLER 377 (MODIFIED) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E377 (modified) ultralight airfoil Max thickness 3.8% at 6.1% chord Max camber 9.2% at 32.6% chord Max Cl/Cd 61.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx60100sm-il) FX60-100 10.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% chord Max Cl/Cd 61.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database