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.

(rc0864c-il) NASA/LANGLEY RC08-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 08-64C rotorcraft airfoil Max thickness 8% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ht23-il) HT23		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT23 airfoil Max thickness 6.5% at 20.8% chord Max camber 1.1% at 22.6% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae2822-il) RAE 2822 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae69ck-il) RAE6-9CK AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s1046-il) S1046 17% (Danny Howell)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1046 airfoil Max thickness 17% at 30.8% chord Max camber 0% at 0% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(n13-il) N-13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-13 airfoil Max thickness 11.8% at 30% chord Max camber 0.1% at 95% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s8025-il) S8025 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8025 low Reynolds number airfoil Max thickness 8% at 22.9% chord Max camber 0.4% at 18.8% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord Max camber 2.3% at 30% chord Max Cl/Cd 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh104-il) MH 104 15.28%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord Max camber 1.9% at 31.1% chord Max Cl/Cd 37.2 at Re# 100,000 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 37.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database