Wing loading distribution Calculator depends on various factors including the aircraft design, wing geometry, and aerodynamic considerations. Typically, it involves integrating the weight distribution over the wing span. One common simplified formula is:
Where:
- is the wing loading at a distance from the centerline of the aircraft,
- is the total weight of the aircraft,
- is the wing area,
- is the rate of change of weight with respect to spanwise distance.
Wing loading distribution Calculator plays a crucial role in determining the aerodynamic performance and stability of an aircraft. At its core, wing loading distribution reflects the balance between lift and weight across different sections of the wing.
 However, this value varies along the wingspan due to design considerations and aerodynamic factors.
Near the fuselage, where the wings attach to the aircraft’s body, the wing loading tends to be higher. This area experiences greater aerodynamic forces and must support a larger portion of the aircraft’s weight. As you move towards the wingtips, wing loading typically decreases.
This decrease is often attributed to the tapering shape of the wings, which reduces the amount of lift required towards the outer edges. Additionally, wingtip devices such as winglets can affect the distribution by altering airflow patterns and reducing induced drag.