Aerodynamic and stress analysis of a manned aircraft wing (NACA 4412 AIRFOIL)‎

الملخص EN

This research involved a study of aerodynamic analysis to determine the load on a wing of a manned aircraft using ANSYS11 software program.

Awing of aircraft at Mach number (M = 0.4) has been modeled in this program to determine the pressure distribution on both wing sides for steady and unsteady states.

The wing has been tested at three angles of attack, namely (0°, 5°, 10°).

The pressure distribution on the wing has been used to evaluate the stress distribution and displacement for the wing structure.

The stress analysis has been carried out for the skin shell of the wing and the internal stiffeners of the wing box.

The result obtained in the present work showed that the maximum Von Misses stress occurs at distance of 0-15 % from the edge of wing, especially at the corners at which spars web extending from the wing and root ribs intersects the wing skin.