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.

(usa45-il) USA 45 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-45 airfoil Max thickness 14.5% at 29.8% chord Max camber 4.1% at 29.8% chord Max Cl/Cd 17.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah83159-il) AH 83-159		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord Max Cl/Cd 17.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx05188-il) WORTMANN FX 05-188 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-188 airfoil Max thickness 18.8% at 37.1% chord Max camber 2.6% at 50% chord Max Cl/Cd 17.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca653218-il) NACA 65(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(3)-218 airfoil Max thickness 18% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 17.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(dae21-il) DAE-21 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE21 low Reynolds number airfoil Max thickness 11.8% at 32% chord Max camber 6.6% at 43.7% chord Max Cl/Cd 17.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe444-il) GOE 444 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 444 airfoil Max thickness 5.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 17.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(marske4-il) MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID tip airfoil (NACA 43012A*.833 hybrid) Max thickness 10.2% at 20% chord Max camber 2.8% at 15% chord Max Cl/Cd 17 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(cp-140-050-gn) Cambered plate C=14% T=5% R=0.96		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=14% Wall thickness=5% Radius=0.963 Max thickness 5.5% at 3.6% chord Max camber 12.2% at 47.7% chord Max Cl/Cd 17 at Re# 50,000 Source Generated
(npl9510-il) NPL 9510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord Max Cl/Cd 17 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Max Cl/Cd 17 at Re# 50,000 Source UIUC Airfoil Coordinates Database