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The various Euler angles relating the three reference frames are important to flight dynamics. Many Euler angle conventions exist, but all of the rotation sequences presented below use the z-y'-x" convention. This convention corresponds to a type of Tait-Bryan angles, which are commonly referred to as Euler angles. This convention is described ...
Best angle of climb (BAOC) airspeed for an airplane is the speed at which the maximum excess thrust is available. Excess thrust is the difference between the total drag of the aircraft, and the thrust output of the powerplant. For a jet aircraft, this speed is very close to the speed at which the total minimum drag occurs.
If a powered aircraft is generating thrust T and experiencing drag D, the difference between the two, T − D, is termed the excess thrust. The instantaneous performance of the aircraft is mostly dependent on the excess thrust. Excess thrust is a vector and is determined as the vector difference between the thrust vector and the drag vector.
Furthermore, it is assumed that thrust equals drag, and the longitudinal equation of motion may be ignored. . The body is oriented at angle (psi) with respect to inertial axes. The body is oriented at an angle (beta) with respect to the velocity vector, so that the components of velocity in body axes are:
To analyze thrust, we take a mathematical perspective. First, an aircraft takes off at some angle with respect to the ground. For a rocket traveling straight "up", this angle would be 90°, or at least close to 90°. For airplanes and most other aircraft, this angle will be much less, generally ranging from 0° to 60°.
Here the current thrust to weight ratio has been denoted by = / and the current angle between the velocity vector and the vertical by = (^), where = /. This results in a coupled system of equations which can be integrated to obtain the trajectory.
The tangent defines the minimum glide angle, for maximum range. The peak of the curve indicates the minimum sink rate, for maximum endurance (time in the air). Without power, a gliding aircraft has only gravity to propel it. At a glide angle of θ, the weight has two components, W.cos θ at right angles to the flight line and W.sin θ parallel ...
Angle of incidence of an airplane wing on an airplane. On fixed-wing aircraft, the angle of incidence (sometimes referred to as the mounting angle [1] or setting angle) is the angle between the chord line of the wing where the wing is mounted to the fuselage, and a reference axis along the fuselage (often the direction of minimum drag, or where applicable, the longitudinal axis).