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.

(sc20412-il) NASA SC(2)-0412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord Max Cl/Cd 21.8 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 21.8 at Re# 50,000 Source Generated
(m2-il) NACA M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-2 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 21.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah79k132-il) AH 79-K-132/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-132/20 airfoil for use with flaps (K) Max thickness 13.2% at 40.2% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 21.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca633218-il) NACA 63(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 24.9% chord Max Cl/Cd 21.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ah88k136-il) AH 88-K-136/16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord Max Cl/Cd 21.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(k2-il) GRUMMAN K-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-2 transonic airfoil (GAC .80-.53-10.3) Max thickness 10.3% at 38.9% chord Max camber 1.3% at 88.3% chord Max Cl/Cd 21.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca16015-il) NACA 16-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 21.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s9033-il) S9033 (7.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord Max Cl/Cd 21.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(r1082t-il) RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord Max camber 3% at 40% chord Max Cl/Cd 21.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database