Details: Dat file: Parser (naca0008-il) NACA 0008 NACA 0008 airfoil Max thickness 8% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format

This NACA airfoil series is controlled by 4 digits e.g. NACA 2412, which designate the camber, position of the maximum camber and thickness. If an airfoil number is NACA MPXX e.g. NACA 2412

Airfoil database search (NACA 4 digit Symmetrical) 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.

Airfoil database search (NACA 4 digit) 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.

Polar details for airfoil (aerofoil)NACA 0006(naca0006-il) Xfoil prediction at Reynolds number 1,000,000 and Ncrit 9

(naca652415a05-il) NACA 65(2)-415 a=0.5 NACA 65(2)-415 a=0.5 airfoil Max thickness 15% at 39.9% chord. Max camber 3% at 45% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format

Details of airfoil (aerofoil)(naca000834-il) NACA 0008-34 NACA 0008-34 airfoil. Airfoil Tools Search 1638 airfoils Tweet. You have 0 airfoils loaded. Your Reynold number range is 50,000 to 1,000,000. Applications. Airfoil database search; My airfoils; Airfoil plotter; Airfoil comparison; Reynolds number calc ...

Create NACA 5 digit airfoil sections to your own specification for use with the tools. Reynolds number calculator Check the Reynolds number range of your wing or blade so you can select the most suitable polar diagrams.

Polar details for airfoil (aerofoil)NACA 0008(naca0008-il) Xfoil prediction at Reynolds number 200,000 and Ncrit 9

Polar details for airfoil (aerofoil)NACA-M1 AIRFOIL(m1-il) Xfoil prediction at Reynolds number 1,000,000 and Ncrit 9