What are the NACA airfoil designation?

What are the NACA airfoil designation?

National Advisory Committee for Aeronautics airfoils. During the late 1920s and into the 1930s, the NACA developed a series of thoroughly tested airfoils and devised a numerical designation for each airfoil — a four digit number that represented the airfoil section’s critical geometric properties.

How is NACA airfoil calculated?

The NACA four-digit wing sections define the profile by: First digit describing maximum camber as percentage of the chord. Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord. Last two digits describing maximum thickness of the airfoil as percent of the chord.

How do you read NACA airfoil numbers?

The NACA four-digit wing sections define the profile by:

1. First digit describing maximum camber as percentage of the chord.
2. Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.
3. Last two digits describing maximum thickness of the airfoil as percent of the chord.

What was the purpose of NACA?

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research.

Why NACA 0012 airfoil is said to be symmetric airfoil?

Explanation: The NACA 0012 airfoil indicates the symmetric airfoil, because an airfoil with no camber, that is with the camber line and chord line co-incident in an airfoil is called a symmetric airfoil. For the NACA 0012 airfoil is with a maximum thickness of 12%.

What are the aerodynamic characteristics of the NACA 0012?

Report presenting the aerodynamic characteristics of the NACA 0012 airfoil section at a range of angles of attack from 0 to 180 degrees. Data were obtained at two different Reynolds numbers depending on whether the airfoil surfaces were smooth or had roughness applied at the leading and trailing edges.

How big is the far field boundary of NACA 0012?

In this case, the provided NACA 0012 airfoil geometry was used, and the chord length was assumed to be 1 meter. Far field boundary was set approximately 50 chord lengths away from the airfoil in all directions.

What is the stall angle of a NACA 0012?

In this project, the aim is to study the behavior of a NACA 0012 airfoil at a Reynolds number of 50,000, at various angles of attack ranging from 0o to 16o. From the literature the stall angle occurs between 10o and 16o.

What kind of grid is used for NACA 0012?

The study was done using three different grid topologies: 1) Structured O-grid, 2) Structured C-H grid, 3) Unstructured T-Rex grid. First of all, we created the grids using grid generation software named Pointwise. In this case, the provided NACA 0012 airfoil geometry was used, and the chord length was assumed to be 1 meter.