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When the weight of the aircraft is at or below the allowable limit(s) for its configuration (parked, ground movement, take-off, landing, etc.) and its center of gravity is within the allowable range, and both will remain so for the duration of the flight, the aircraft is said to be within weight and balance. Different maximum weights may be ...
The aerodynamic efficiency has a maximum value, E max, respect to C L where the tangent line from the coordinate origin touches the drag coefficient equation plot. The drag coefficient, C D , can be decomposed in two ways.
A space vehicle's flight is determined by application of Newton's second law of motion: =, where F is the vector sum of all forces exerted on the vehicle, m is its current mass, and a is the acceleration vector, the instantaneous rate of change of velocity (v), which in turn is the instantaneous rate of change of displacement.
In steady level longitudinal flight, thrust counterbalances drag and lift supports the aircraft's weight. Lift and drag are components of the aerodynamic force. Steady flight , unaccelerated flight , or equilibrium flight is a special case in flight dynamics where the aircraft's linear and angular velocity are constant in a body-fixed reference ...
is the weight. Since the load factor is the ratio of two forces, it is dimensionless. However, its units are traditionally referred to as g, because of the relation between load factor and apparent acceleration of gravity felt on board the aircraft. A load factor of one, or 1 g, represents conditions in straight and level flight, where the lift ...
On earth, weight is fairly easy to calculate: = In this equation, m represents the mass of the object and g is the acceleration that is produced by gravity. On earth, this value is approximately 9.8 m/s squared. When the force for lift is greater than the force of weight, the aircraft accelerates upwards.
The Monarch Butterfly has a very low 0.168 kg/m 2 wing loading The McDonnell Douglas MD-11 has a high 837 kg/m 2 maximum wing loading. In aerodynamics, wing loading is the total weight of an aircraft or flying animal divided by the area of its wing.
Additionally, Bernoulli's equation is a solution in one dimension to both the momentum and energy conservation equations. The ideal gas law or another such equation of state is often used in conjunction with these equations to form a determined system that allows the solution for the unknown variables. [20]