Author name: Kalpana Southri

In flight mechanics, the “angle of attack at the wing” refers to the angle between the chord line of the wing and the relative wind experienced by the wing. This angle is known as the “effective angle of attack” at the wing and is denoted as αw. αw: Effective angle of attack at the wing. […]

The relative wind is defined in relation to the aircraft’s flight path. It’s the direction in which the oncoming air flows over the aircraft’s surfaces, particularly the wings and control surfaces. The relative wind is not necessarily the same as the actual wind that’s blowing in the atmosphere, as the aircraft’s own motion contributes to

The pitching moment coefficient is a dimensionless parameter that represents the aircraft’s tendency to rotate around its lateral (pitch) axis due to changes in angle of attack. It’s defined as the ratio of the pitching moment to the dynamic pressure, reference area, and reference length. Cmcg = (Mcg / (0.5 * ρ * v^2 *

The equation you’ve provided is known as the Reynolds number equation, which is used in fluid dynamics to characterize the flow of a fluid (liquid or gas) around an object, such as an aircraft, by comparing the inertial forces to the viscous forces within the fluid. This dimensionless number helps classify the type of flow

Coriolis acceleration is a concept in flight mechanics and physics that arises due to the rotation of the Earth. It is a fictitious or apparent acceleration experienced by objects moving in a rotating reference frame, such as the Earth’s surface. Coriolis acceleration is important in various fields, including meteorology, oceanography, and, indeed, flight mechanics. V

Newton’s second law refers to the fundamental principle that governs the motion of an aircraft or any other object in a fluid medium (such as air). It states that the force acting on an object is directly proportional to the rate of change of its momentum and occurs in the direction of the applied force

At the bottom of the loop, the aircraft is usually experiencing maximum positive G-forces (acceleration) pushing the pilot and the aircraft downward. The lift force provided by the wings must counteract the increased weight due to these G-forces, along with the aircraft’s normal weight.  L means lift required is maximum at the bottom of the

Dynamic pressure (often denoted as q) is a fundamental concept used to describe the kinetic energy per unit volume of a moving fluid, such as air in the case of aircraft in flight. It plays a crucial role in understanding and analyzing the aerodynamic forces acting on an aircraft. Dynamic pressure is defined as: q=1/2*ρ*V^2

The density ratio is essential for understanding the changes in air density with varying altitude, temperature, and pressure. It plays a crucial role in various aerodynamic calculations, including lift, drag, thrust, and engine performance. σ=ρ/​ρ0​ Where: ρ is the air density at a specific altitude or condition. ρ0​ is the air density at the reference

The estimation of landing distance in flight mechanics refers to the process of calculating the distance required for an aircraft to decelerate, descend, and come to a complete stop after touching down on a runway during the landing phase. This is a critical aspect of aviation safety and performance assessment, as it ensures that the