Flight Mechanics

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In aeronautics, wave drag is a component of the aerodynamic drag on aircraft wings and fuselage, propeller blade tips and projectiles moving at transonic and supersonic speeds, due to the presence of shock waves123. At zero angle of attack, the symmetrical airfoil produces no lift. Thus, a positive angle of attack is required if the

Geopotential altitude is a vertical coordinate referenced to Earth’s mean sea level. It is an adjustment to geometric altitude, which is the altitude as measured from the mean sea level. Geopotential altitude accounts for the variation of gravity with latitude and altitude. ‘R ’ is the radius of earth and ‘hG’ is the geometric altitude

The kinematic viscosity is defined as the ratio of the dynamic viscosity (μ) to the density (ρ) of the fluid. μ = dynamic viscosity (also known as absolute viscosity) ρ = density of the fluid ν = kinematic viscosity

In flight mechanics, the fineness ratio is the ratio of the length of a body to its maximum width1. In naval architecture and aerospace engineering, the fineness ratio is the ratio of the length of a body to its maximum width. Af is the fineness ratio of the fuselage. l is the length of the fuselage.

In flight mechanics, takeoff parameter is a term used to describe the factors that affect the takeoff of an aircraft. The takeoff parameter consists of three important factors: thrust, weight, and wing area1. The takeoff distance consists of two parts, the ground run, and the distance from where the vehicle leaves the ground to until it

Pitching moment coefficient (Cm) is a dimensionless parameter that relates the pitching moment of an aircraft to various factors affecting its stability and control. It is an important aerodynamic coefficient used to understand how the aircraft behaves in pitch (upward or downward rotation) around its lateral axis.  M is the pitching moment acting on the

The term “polar” refers to the polar curve, which is a graphical representation of an aircraft’s performance characteristics. In aviation, the most common polar curve is the lift coefficient versus drag coefficient curve, often referred to as the “lift-drag polar.” Cd = Cd0 + (Cl^2 / (π * e * A)) Cd: Total drag coefficient,

stalling speed (Vs) refers to the minimum speed at which an aircraft can maintain level flight without stalling. Stalling occurs when the critical angle of attack is exceeded, and the airflow over the wings becomes separated, leading to a loss of lift and a significant decrease in the aircraft’s performance. Vs​ is the speed of

C is the chord L is the lift force generated by the wing. ρ (rho) is the air density. V is the airspeed (velocity) of the aircraft relative to the air N is Normal force