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.

(fx711525-il) FX 71-L-150/25 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-150/25 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 50.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n0011sc-il) NACA/LANGLEY SYMMETRICAL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 11% symmetrical supercritical airfoil Max thickness 11% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 50.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e230-il) E230 (9.96%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E230 airfoil Max thickness 10% at 29.3% chord Max camber 0% at 0% chord Max Cl/Cd 50.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx71120-il) WORTMANN FX 71-120 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-120 airfoil Max thickness 12% at 25% chord Max camber 0% at 0% chord Max Cl/Cd 50.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc20406-il) NASA SC(2)-0406 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0406 airfoil (NASA TP-2969) Max thickness 6% at 35% chord Max camber 0.6% at 79% chord Max Cl/Cd 50.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 50.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq07-il) HQ 0/7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/7 R/C sailplane airfoil Max thickness 7% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 50.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca0008-il) NACA 0008		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 50.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc20503-il) NASA SC(2)-0503 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0503 airfoil (NASA TP-2969) Max thickness 3% at 32% chord Max camber 0.8% at 82% chord Max Cl/Cd 50.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ht12-il) HT12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord Max Cl/Cd 50.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database