Author name: Kalpana Southri

In flight mechanics, the yawing moment due to the roll rate refers to the rotational force or moment that is generated around the vertical axis of an aircraft (yaw axis) as a result of a change in the aircraft’s roll rate. This phenomenon is a consequence of the complex interactions between the aircraft’s aerodynamic surfaces, […]

The rate of change of pitching moment due to the aircraft’s pitch rate is a measure of how the pitching moment (a turning force) on an aircraft changes as the aircraft’s pitch angle changes over time. This is often denoted as “Cm_q” and is related to the aircraft’s stability and control characteristics. “M q” is

In flight mechanics, “pitching moment” refers to the rotational force that causes an aircraft to pitch (rotate) nose-up or nose-down around its lateral axis. It’s one of the three rotational movements in flight, along with roll (rotation around the longitudinal axis) and yaw (rotation around the vertical axis). Mw​ represents the pitching moment acting on

In flight mechanics, the “vertical force” acting on an aircraft refers to the force that acts vertically, perpendicular to the aircraft’s flight path and the Earth’s surface. This force is essential for maintaining the aircraft’s altitude and controlling its vertical motion, including climbing, descending, and level flight. Zw​ represents the vertical force acting on the

In flight mechanics, the drag force acting on an aircraft in the horizontal direction is a force that opposes the aircraft’s forward motion through the air. This force is caused by various factors, including air resistance due to the aircraft’s shape, air viscosity, and other aerodynamic effects. The drag force is a key parameter in

In flight mechanics, “climb speed” refers to the rate at which an aircraft gains altitude vertically, often expressed in units of velocity (such as meters per second or feet per minute). Climb speed is a key parameter that describes the aircraft’s ability to ascend or descend within a given time frame. It’s an important concept

“lift” refers to the force that counteracts the weight of an aircraft and allows it to maintain level flight. Level flight occurs when an aircraft is flying horizontally at a constant altitude, neither climbing nor descending. ρ (rho) represents the air density. V0​ represents the velocity of the aircraft relative to the air. S represents

In flight mechanics and aerodynamics, the moment coefficient associated with control surfaces refers to the change in the aircraft’s pitching moment (rotation around its lateral axis) caused by the deflection or movement of a specific control surface, such as an aileron, elevator, or rudder. Control surfaces are movable parts on an aircraft’s wings and tail

The lift coefficient during cruise in flight mechanics refers to the value of the coefficient of lift (CL) that an aircraft sustains while flying in its normal, non-manoeuvring, and level flight condition. Cruise flight is typically associated with steady flight at a constant velocity and altitude, where the lift generated by the aircraft’s wings is

The angle of attack at which an airfoil does not produce any lift. Its value is generally less than zero unless the airfoil is symmetric α0L: The zero-lift angle of attack. This is the angle of attack at which the aircraft’s wing generates zero lift. It’s an important parameter that affects the overall aerodynamic behavior of the aircraft. CLcr: The coefficient of lift at the critical point. The critical point is typically associated with the point at which the