Max thickness 17.9% at 34.8% chord.

Airfoil (aerofoil) plot of NACA 64(3)-618 with ajustable chord width, camber and thickness and full size print out

Figure A-1 shows data for the NACA 0012 airfoil, a classic symmetrical shape that is used for everything from airplane stabilizers and canards to helicopter rotors to submarine “sails”. Note that for the symmetrical shape the lift coefficient is zero at zero angle of attack.

Wind tunnel data from NACA TR-824 as digitized by Gregory P.D. Siemens in 1994 at the University of Saskatchewan. The digitized TR-824 data has been processed and interpolated to generate all the plots and can not be guaranteed to be an exact match to the TR-824 plots.

Sep 1, 2022 · In this paper, measurements of the stall of a NACA 64 (3) – 418 airfoil section are presented and compared to a simulation with a hybrid Reynolds-averaged Navier–Stokes (RANS)/large-eddy simulation (LES) model with the goal of gaining deeper insight into the flow physics of a stall cell and the turbulent wake in such conditions. Detailed ...

Team Morphics has developed a novel, compliant, and shape morphing airfoil, with actuated dimple structures on the leading edge. The compliant airfoil can morph its shape between different NACA profiles, and delay boundary layer flow separation …

The scope of this paper is to perform a detailed analysis of the unsteady flow properties in proximity of the trailing-edge of a lifting free transition NACA 64-618 extruded airfoil.

The shape of the NACA airfoils is described using a series of digits following the word "NACA"

With this objective, first different Computational Fluid Dynamics (CFD) simulations are conducted to gather data about the tested case. Then, a numerical model based on Artificial Neural Networks...

Max thickness 17.9% at 34.7% chord.