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.

(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 147.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe06k-il) GOE 6K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 6K airfoil Max thickness 7.5% at 50% chord Max camber 3.1% at 50% chord Max Cl/Cd 147.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx66s171-il) FX 66-S-171 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-171 airfoil Max thickness 17.1% at 33.9% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 147.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx63120-il) FX 63-120 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-120 airfoil Max thickness 12% at 30.8% chord Max camber 5.2% at 50% chord Max Cl/Cd 147.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s831-nr) NREL's S831 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord Max camber 5% at 53.1% chord Max Cl/Cd 147.5 at Re# 1,000,000 Source NWTC National WInd Technology Center

(fx78k140a20-il) FX 78-K-140 A/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-K-140 airfoil for use with flaps (K) A/20 Max thickness 14.1% at 43.5% chord Max camber 4.4% at 43.5% chord Max Cl/Cd 147.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa98-il) USA 98 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-98 airfoil Max thickness 14.3% at 30% chord Max camber 6.4% at 50% chord Max Cl/Cd 147.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx73170-il) WORTMANN FX 73-170		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-170 airfoil Max thickness 17.1% at 43.5% chord Max camber 4.4% at 56.5% chord Max Cl/Cd 147.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe332-il) GOE 332 (PFALZ 61) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 332 (Pfalz 61) airfoil Max thickness 11.8% at 29.8% chord Max camber 6.4% at 39.8% chord Max Cl/Cd 147.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s801-nr) NREL's S801 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S801 primary 13.5% Not recommended Max thickness 13.5% at 37.8% chord Max camber 3.7% at 47.1% chord Max Cl/Cd 147.3 at Re# 1,000,000 Source NWTC National WInd Technology Center