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.

(cp-160-050-gn) Cambered plate C=16% T=5% R=0.86		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=16% Wall thickness=5% Radius=0.861 Max thickness 5.2% at 3.4% chord Max camber 14.3% at 49.2% chord Max Cl/Cd 15.1 at Re# 50,000 Source Generated
(goe765-il) Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Used on the Me163 Komet Max thickness 14.4% at 30% chord Max camber 1.9% at 25.9% chord Max Cl/Cd 15.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx78k161-il) FX 78-K-161		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-K-161 airfoil for use with flaps (K) Max thickness 16.2% at 40.2% chord Max camber 2.8% at 37.1% chord Max Cl/Cd 15.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq300gd2-il) HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	DFVLR/Braunschweig Horstmann and Quast HQ-300 GD(MOD 2) sailplane airfoil Max thickness 16.6% at 39.1% chord Max camber 3.9% at 39.1% chord Max Cl/Cd 15.1 at Re# 50,000 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 15.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord Max camber 3.7% at 63.4% chord Max Cl/Cd 15 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e547-il) EPPLER 547 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E547 general aviation airfoil Max thickness 17.4% at 40.3% chord Max camber 2% at 30.7% chord Max Cl/Cd 15 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx78k140-il) FX 78-K-140/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-K-140/20 airfoil for use with flaps (K) Max thickness 14.1% at 43.5% chord Max camber 4.4% at 43.5% chord Max Cl/Cd 15 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca643618-il) NACA 64(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord Max Cl/Cd 14.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah80136-il) AH 80-136		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-136 airfoil Max thickness 13.5% at 33.9% chord Max camber 3.4% at 33.9% chord Max Cl/Cd 14.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database