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.

(naca671215-il) NACA 67		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 67 Max thickness 15% at 50% chord Max camber 1.1% at 50% chord Max Cl/Cd 33.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca23024-il) NACA 23024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23024 airfoil Max thickness 24% at 30.3% chord Max camber 2.9% at 1.3% chord Max Cl/Cd 33.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ht08-il) HT08		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT08 airfoil Max thickness 5% at 20.2% chord Max camber 0% at 0% chord Max Cl/Cd 33.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe571-il) GOE 571 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 571 airfoil Max thickness 24.9% at 29.4% chord Max camber 9.8% at 29.4% chord Max Cl/Cd 33.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx3-il) WORTMANN FX 3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord Max Cl/Cd 32.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(m1-il) NACA-M1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-1 airfoil Max thickness 6.2% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 32.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(du861372-il) DU 86-137/25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Delft University DU 86-137/25 Airfoil Max thickness 13.6% at 41.6% chord Max camber 0.3% at 1.6% chord Max Cl/Cd 32.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e862-il) EPPLER 862 STRUT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E862 strut airfoil Max thickness 32.4% at 28.5% chord Max camber 0% at 0% chord Max Cl/Cd 32.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20403-il) NASA SC(2)-0403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0403 airfoil (NASA TP-2969) Max thickness 3% at 36% chord Max camber 0.6% at 85% chord Max Cl/Cd 32.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr9-il) BOEING-VERTOL VR-9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-9 rotorcraft airfoil Max thickness 6.1% at 35% chord Max camber 0.3% at 35% chord Max Cl/Cd 32.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database