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x b axis - positive out the nose of the aircraft in the plane of symmetry of the aircraft; z b axis - perpendicular to the x b axis, in the plane of symmetry of the aircraft, positive below the aircraft; y b axis - perpendicular to the x b,z b-plane, positive determined by the right-hand rule (generally, positive out the right wing) Wind frame
Flight dynamics is the science of air-vehicle orientation and control in three dimensions. The critical flight dynamics parameters are the angles of rotation with respect to the three aircraft's principal axes about its center of gravity, known as roll, pitch and yaw.
Aircraft flight mechanics are relevant to fixed wing (gliders, aeroplanes) and rotary wing (helicopters) aircraft.An aeroplane (airplane in US usage), is defined in ICAO Document 9110 as, "a power-driven heavier than air aircraft, deriving its lift chiefly from aerodynamic reactions on surface which remain fixed under given conditions of flight".
A sample CG-moment envelope chart, showing that a loaded plane weighing 2,367 lb (1,074 kg) with a moment of 105,200 lb⋅in (11886 N⋅m) is within the "normal category" envelope. Center of gravity (CG) is calculated as follows: Determine weights and arms for all mass within the aircraft. Multiply weights by arms for all mass to calculate moments.
Cockpit controls and instrument panel of a Cessna 182D Skylane. Generally, the primary cockpit flight controls are arranged as follows: [2] A control yoke (also known as a control column), centre stick or side-stick (the latter two also colloquially known as a control or joystick), governs the aircraft's roll and pitch by moving the ailerons (or activating wing warping on some very early ...
Mean aerodynamic chord (MAC) is defined as: [6] = (), where y is the coordinate along the wing span and c is the chord at the coordinate y.Other terms are as for SMC. The MAC is a two-dimensional representation of the whole wing. The pressure distribution over the entire wing can be reduced to a single lift force
The weight of the aircraft is the common factor that links all aspects of aircraft design such as aerodynamics, structure, and propulsion, all together. An aircraft's weight is derived from various factors such as empty weight, payload, useful load, etc. The various weights are used to then calculate the center of mass of the entire aircraft. [37]
These results obtained are calculated using the thin airfoil theory so the use of the results are warranted only when the assumptions of thin airfoil theory are realistic. In precision experimentation with real airfoils and advanced analysis, the aerodynamic center is observed to change location slightly as angle of attack varies.