(m9-il) NACA M9 AIRFOIL NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord. Max camber 7.2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format: NACA M9 AIRFOIL 17. 17. 0.0000000 0.0000000 0.0125000 0.0312000 0.0250000 0.0459000 0.0500000 0.0639000 0.0750000 0.0779000 0.1000000 0.0885000 ...

NACA M9 AIRFOIL DB Name: m9 Family: NACA/Munk Max thickness: 10.4% at x = 16.96% chord Max camber: 7.3% at x = 33.84% chord Available data sources: JavaFoil+Calcfoil stall+Eppler

Direct link: NACA M9 Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord

The NACA airfoil series is a set of standardized airfoil shapes developed by this agency, which became widely used in the design of aircraft wings. Origins [ edit ]

naca m9 airfoil 17. 17. 0.0000000 0.0000000 0.0125000 0.0312000 0.0250000 0.0459000 0.0500000 0.0639000 0.0750000 0.0779000 0.1000000 0.0885000 0.1500000 0.1011000 0.2000000 0.1075000 0.2500000 0.1111000 0.3000000 0.1110000 0.4000000 0.1024000 0.5000000 0.0878000 0.6000000 0.0695000 0.7000000 0.0484000 0.8000000 0.0294000 0.9000000 0.0122000 1.0000000 0.0000000 0.0000000 0.0000000 0.0125000 ...

See the Airfoil ClCdCm Database for a list of airfoils which can be used with nlll. You are encouraged to add airfoil coordinates to this database. To do so, construct a plain text (.txt) file with two columns (x/c and y/c), running from the upper trailing edge to …

Polar details for airfoil (aerofoil)NACA M9 AIRFOIL(m9-il) Xfoil prediction at Reynolds number 50,000 and Ncrit 9

These airfoils, de&i9- naled the NAGA 16-8eries, have increased critical Mach num- ber. The methods by these airfoils hate been developed are applicable to other airplane components.

The early NACA airfoil series, the 4-digit, 5-digit, and modified 4-/5-digit, were generated using analytical equations that describe the camber (curvature) of the mean-line (geometric centerline) of

The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word "NACA".