Which NACA airfoil produces the most lift?
The NACA 230-series airfoils with thickness ratio less than 20% generally achieve the highest maximum lift coefficients. The maximum lift coefficient with flaps is about the same for moderately thick 6-series airfoils as it is for the NACA 23012 with flaps.
What is the maximum thickness of a 60 inch chord wing using a NACA 4415 airfoil?
NACA 4415 – NACA 4415 airfoil Max thickness 15% at 30.9% chord.
What is the maximum thickness for a NACA 0012 airfoil?
12%
NACA0012 airfoil is a symmetrical low lift airfoil with maximum thickness being 12% of the chord located at 30% of the chord length.
Which NACA airfoil is best?
There is no single airfoil that will always create more lift than another airfoil. The amount of lift that an airfoil creates has to do with the angle of attack, speed, and other flight conditions. Different airfoils work well in different conditions. A very common NACA airfoil is the NACA 4412.
What is the best airfoil shape?
The most efficient airfoil for producing the greatest lift is one that has a concave or “scooped out” lower surface. As a fixed design, this type of airfoil sacrifices too much speed while producing lift and is not suitable for high-speed flight.
What airfoil should I use?
If the plane is to be a precision aerobat then a symmetrical airfoil is most appropriate because it flies the same in any given attitude. If the plane is to fly slowly or carry a load but is not intended to do aerobatics then a flat-bottom or under-cambered airfoil should be considered.
How are the airfoils in the NACA series generated?
The NACA airfoil series 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 airfoil section as well as the section’s thickness distribution along the length of the airfoil.
What is the maximum thickness of a NACA 2415 airfoil?
For example, the NACA 2415 airfoil has a maximum thickness of 15% with a camber of 2% located 40% back from the airfoil leading edge (or 0.4c). Utilizing these m, p, and t values, we can compute the coordinates for an entire airfoil using the following relationships: 1. Pick values of x from 0 to the maximum chord c. 2.
What do the numbers mean on an airfoil?
The first digit specifies the maximum camber (m) in percentage of the chord (airfoil length), the second indicates the position of the maximum camber (p) in tenths of chord, and the last two numbers provide the maximum thickness (t) of the airfoil in percentage of chord.
Is the NACA 5 Digit Series the same as the four digit series?
NACA Five-Digit Series: The NACA Five-Digit Series uses the same thickness forms as the Four-Digit Series but the mean camber line is defined differently and the naming convention is a bit more complex. The first digit, when multiplied by 3/2, yields the design lift coefficient (c l) in tenths.