What is the thickness ratio of NACA 23012?

For example, the NACA 23012 has a maximum thickness of 12\%, a design lift coefficient of 0.3, and a maximum camber located 15\% back from the leading edge.

What does NACA 0012 mean?

NACA 0012 mean that there is no camber i.e. zero camber is present, and it has the maximum thickness of the airfoil at 12\% of the chord from the leading edge.

What is NACA series?

The shape of the NACA airfoils is described using a series of digits following the word “NACA”. The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties.

What is the NACA 0012 airfoil used for?

NACA0012 airfoil was used for all configurations due to availability of experimental lift and drag data. Lift, drag and pressure coefficient were calculated with SST turbulence model at the Reynolds numbers of 6 × 10⁶ and were compared with experimental data to validate the simulation accuracy of numerical approaches.

What is the chord length of NACA 0012?

The chord length is 1 m. The width of the first cell at the airfoil boundary is 0.02 mm.

What is NACA 6 Series?

The NACA 6-series and 6A-series airfoils are defined by means of conformal transformations. These relate the flow over an airfoil to that of a near-circle and that to a circle. These functions are multiplied by a scale factor to produce airfoils of various thickness to chord ratios.

What does an airfoil do?

An airplane’s wing has a special shape called an airfoil. The airfoil is shaped so that the air traveling over the top of the wing travels farther and faster than the air traveling below the wing. Thus, the faster moving air above the wing exerts less pressure than the slower moving air below the wing.

What is the measured lift slope for the NACA 23012 airfoil?

The measured lift slope for the NACA 23012 airfoil is 0.1080 degree -1, and αL=0 = -1.3°. Consider a finite wing using this airfoil, with AR = 8 and taper ratio = 0.8.

What does the NACA 23112 profile measure?

For example, the NACA 23112 profile describes an airfoil with design lift coefficient of 0.3 (0.15*2), the point of maximum camber located at 15\% chord (5*3), reflex camber (1), and maximum thickness of 12\% of chord length (12). By this point, they had more confidence in their ability to predict performance rather than simply measuring it.

What is the camber of the NACA 2412?

So the NACA 2412 has 2\% camber occuring at 40\% of the chord behind the leading edge and has a maximum thickness that is 12\% of the chord. Here is a diagram showing it:

How thick is NACA 2412 airfoil?

The final two digits of each airfoil were the maximum thickness. Thus NACA 2412 is a 12\% thick, subsonic airfoil of the 2400 family. (2400 was probably either uncanbered or very modest camber with Max thickness fairly far forward. That is from 60 years of memory so do not bet on it…)