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.

(boe103-il) BOEING 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 103 airfoil Max thickness 12.7% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh32-il) MH 32 8.7%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 32 for F3E and F3B Max thickness 8.7% at 30.2% chord Max camber 2.3% at 45.7% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe275-il) GOE 275 (DAIMLER VI) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 275 (DAIMLER VI) airfoil Max thickness 7.7% at 19.9% chord Max camber 4.7% at 29.9% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca6412-il) NACA 6412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6412 airfoil Max thickness 12% at 30.1% chord Max camber 6% at 39.6% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag25-il) AG25 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG25 airfoil used on the Bubble Dancer R/C DLG Max thickness 7.6% at 24.7% chord Max camber 2.4% at 45.4% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe406-il) GOE 406 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 406 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.5% at 39.9% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe433-il) GOE 433 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 433 airfoil Max thickness 17.4% at 29.2% chord Max camber 4.8% at 49.2% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m15-il) NACA M15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(stcyr24-il) St. CYR 24 (Bartel 35-IIIC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 24 (Bartel 35-IIIC) airfoil Max thickness 12.4% at 30% chord Max camber 5.9% at 40% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n11h9-il) NACA 11-H-09 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 11-H-9 rotorcraft airfoil Max thickness 9% at 40.2% chord Max camber 4.5% at 30% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database