Flight Mechanics

In flight mechanics, the “boundary layer” is a thin layer of air that forms near the surface of an aircraft’s wing or other aerodynamic surfaces as it moves through the air. This layer of air experiences a gradual transition from the free-stream airflow (far away from the surface) to a velocity of zero at the […]

In flight mechanics and aerodynamics, the coefficient of drag (CD) with respect to angle of attack refers to how the drag force acting on an airfoil or wing changes as the angle of attack (α) is varied. Cn sin(alpha)+Cc cos(alpha) Cn: The normal force coefficient, which represents the lift force component perpendicular to the relative

CL” stands for the “Coefficient of Lift.” It is a dimensionless quantity that represents the lift generated by an airfoil or wing at a specific angle of attack. The coefficient of lift is a crucial parameter in understanding and analyzing the aerodynamic performance of an aircraft. Cn cos(alpha)-Cc sin(alpha) Cn: The normal force coefficient, which

The “Coefficient of Lift” (CL) is a dimensionless parameter that represents the lift force generated by an airfoil or wing relative to the dynamic pressure of the airflow. The coefficient of lift is defined as the ratio of the lift force (L) acting on the airfoil or wing to the dynamic pressure (q) and the

Average fuel per hour” refers to the rate at which an aircraft consumes fuel over a given time period of one hour. It is typically expressed in terms of fuel flow rate, measured in pounds per hour (lb/hr), gallons per hour (gal/hr), liters per hour (L/hr), or other relevant units of mass or volume per

In flight mechanics, the “drag coefficient” (CD) in turning flight refers to the dimensionless parameter that quantifies the drag force acting on an aircraft during a turn. It is a crucial factor in understanding the aerodynamic performance of the aircraft while maneuvering. Ta / (0.5 * ρ * V^2 * S) Ta: Thrust force acting

True Airspeed” (TAS) refers to the actual speed of an aircraft through the surrounding air. It is the speed of the aircraft relative to the undisturbed air in which it is flying, and it is measured in knots (nautical miles per hour) or meters per second (m/s). V = Ve / √(σ) V: True Airspeed

In flight mechanics, “lift during climb” refers to the aerodynamic force that opposes the weight of an aircraft while it is ascending vertically or at an upward angle. During climb, the aircraft is gaining altitude and increasing its potential energy, which requires an additional lift force to overcome gravity and maintain a positive rate of

In flight mechanics and aviation, the “Flight Mach Number” is a dimensionless parameter used to express an aircraft’s speed relative to the speed of sound in the surrounding air. It is a critical parameter in high-speed flight and is denoted by the symbol “M.” The Flight Mach Number is defined as the ratio of the

Drag in climb refers to the aerodynamic force that acts opposite to the direction of motion of an aircraft while it is ascending vertically or at an upward angle (climbing). Drag is one of the aerodynamic forces that an aircraft must overcome during climb to maintain a positive rate of climb. D = (1/2) ρ