Airfoil Tools
Search 1638 airfoils

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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.

(hq259-il) HQ 2.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 80 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe371-il) GOE 371 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 371 airfoil Max thickness 7% at 29.9% chord Max camber 4.6% at 39.9% chord Max Cl/Cd 80 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh112-il) MH 112 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 112 for a propeller for ultralight (root) Max thickness 16.2% at 31.8% chord Max camber 6.7% at 48.5% chord Max Cl/Cd 80 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr5-il) BOEING-VERTOL VR-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-5 rotorcraft airfoil Max thickness 12% at 35% chord Max camber 3.4% at 35% chord Max Cl/Cd 79.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe400-il) GOE 400 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 400 airfoil Max thickness 6.1% at 20% chord Max camber 4.9% at 40% chord Max Cl/Cd 79.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(usa41-il) USA 41 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-41 airfoil Max thickness 6.6% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 79.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx62k153-il) FX 62-K-153/20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 62-K-153/20 airfoil Max thickness 15.3% at 40.2% chord Max camber 4.1% at 62.9% chord Max Cl/Cd 79.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e817-il) EPPLER 817 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E817 hydrofoil Max thickness 11% at 32.9% chord Max camber 2.9% at 66.7% chord Max Cl/Cd 79.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe801-il) GOE 801 (MVA 301) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 801 (MVA 301) airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 79.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe802-il) GOE 802 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 79.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database