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.

(goe142-il) GOE 142 (MVA H.19) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 142 (MVA H.19) airfoil Max thickness 6.2% at 24.9% chord Max camber 3.8% at 34.9% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63412-il) NACA 63-412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe147-il) GOE 147 (MVA H.6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 147 (MVA H.6) airfoil Max thickness 7.5% at 14.9% chord Max camber 3.8% at 29.9% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sd6080-il) SD6080 (9.2%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD6080 low Reynolds number airfoil Max thickness 9.2% at 30.9% chord Max camber 3.2% at 44.7% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca2410-il) NACA 2410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2410 airfoil Max thickness 10% at 29.9% chord Max camber 2% at 40% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe328-il) GOE 328 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 328 airfoil Max thickness 8.2% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq2512-il) HQ 2.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sc21010-il) NASA SC(2)-1010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-1010 airfoil Max thickness 10% at 32% chord Max camber 2.8% at 71% chord Max Cl/Cd 36.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag38-il) AG38		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG38 airfoil Max thickness 7% at 27.7% chord Max camber 2% at 36.7% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n22-il) N-22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-22 airfoil Max thickness 12.4% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database