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.

(doa5-il) DORNIER A-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% chord Max Cl/Cd 25.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx711520-il) FX 71-L-150/20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/20 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 25.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx76100-il) WORTMANN FX 76-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-100 symmetrical airfoil Max thickness 10.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 25.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1012-il) S1012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord Max camber 0% at 0% chord Max Cl/Cd 25.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e639-il) EPPLER 639 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E639 airfoil Max thickness 12.6% at 29.2% chord Max camber 4.8% at 29.2% chord Max Cl/Cd 25.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(e556-il) EPPLER 556 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E556 general aviation airfoil Max thickness 16% at 31.1% chord Max camber 3.1% at 61.4% chord Max Cl/Cd 25.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e837-il) EPPLER E837 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E837 hydrofoil Max thickness 16.1% at 36.9% chord Max camber 0% at 0% chord Max Cl/Cd 25.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nacam2-il) NACA M2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M2 airfoil Max thickness 8.1% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 25.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord Max Cl/Cd 25.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord Max Cl/Cd 25.5 at Re# 50,000 Source Generated