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TEST BORRADO, QUIZÁS LE INTERESE: 3272-8 Aero (8.9)

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Título del Test: 3272-8 Aero (8.9) Descripción: 3272-8 Aero (8.9) Autor: atom OTROS TESTS DEL AUTOR Fecha de Creación: 14/10/2024 Categoría: Otros Número Preguntas: 52

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Drooping of helicopter blades is compensated by flapping. dragging. centrifugal force. With a drop in ambient temperature, an aircraft service ceiling will lower. rise. not be affected. Climbs with forward speed require less power than vertical climbs, because of translational lift. increased inertia. forward momentum. Tracking is carried out to_____________the main rotor blade tip path. restore. align. balance. What principle does the delta 3 hinge use? Triangular pitch change lever. Flapping actuators. Offset hinges. The bell stability augmentation system is based on flapping hinges. offset hinges. gyroscopic forces. The difference between transient droop and static droop is overswing. underswing. a hole in one. An helicopter fin helps to give longitudinal stability about the normal axis. directional stability about the normal axis. directional stability about the longitudinal axis. Solidity of the rotor is the ratio of the blade area to disc area. all up weight to blade area. all up weight to disc area. Lift in a helicopter is a result of pitch * square root of speed. angle of attack * velocity squared. angle of attack * velocity squared and forward speed. The layer of air over the surface of an aerofoil which is slower moving, in relation to the rest of the airflow, is known as camber layer. boundary layer. none of the above are correct. When airflow velocity over an upper cambered surface of an aerofoil decreases, what takes place? Pressure increases, lift decreases. Pressure decreases, lift increases. Pressure increases, lift increases. What is a controlling factor of turbulence and skin friction? Countersunk rivets used on skin exterior. Fineness ratio. Aspect ratio. Changes in aircraft weight will only affect total drag if the lift is kept constant. will not affect total drag since it is dependant only upon speed. cause corresponding changes in total drag due to the associated lift change. When an aerofoil stalls lift and drag increase. lift decreases and drag increases. lift increases and drag decreases. Translational drift is the tendency for the aircraft to drift laterally. the tendency for the aircraft to turn to port. the tendency for the aircraft to pitch nose up. The tropopause exists at about 18,000 ft. 30,000 ft. 36,000 ft. The centre of pressure of an aerofoil is that point on the cord line which moves most, with changes in angle of attack, if the section is symmetrical. at which the highest pressure is said to act. at which the lift forces resultant is said to act. Dihedral wings combat instability in yaw. side-slip. pitch. An aircraft, which is longitudinally stable, will tend to return to level flight after a movement in which axis? Pitch. Yaw. Roll. The normal axis of an aircraft passes through the centre of gravity. a point at the centre of the wings. at the centre of pressure. Due to the change in downwash on an untapered wing (i.e. one of constant chord length) it will not provide any damping effect when rolling. not suffer adverse yaw effects when turning. tend to stall first at the root. Correcting for a disturbance which has caused a rolling motion about the longitudinal axis would re- establish which of the following? Lateral stability. Longitudinal stability. Directional stability. Porpoising is an oscillatory motion in the yaw plane. roll plane. pitch plane. Directional stability is maintained by the tailplane, and controlled by the elevators. by the keel surface and fin, and controlled by the rudder. by the mainplanes, and controlled by the ailerons. Longitudinal stability is given by the fin. the wing dihedral. the horizontal tailplane. Lateral stability is given by the horizontal tailplane. the ailerons. the wing dihedral. Stability about the lateral axis is given by the ailerons. the horizontal tailplane. wing dihedral. Sweepback of the wings will decrease lateral stability. not affect the lateral stability. increase lateral stability. Dutch Roll is primarily a pitching instability. a combined rolling and yawing motion. a type of slow roll. A high wing position gives more lateral stability than a low wing. less lateral stability than a low wing. the same lateral stability as a low wing. Directional stability may be increased with pitch dampers. horn balance. yaw dampers. Lateral stability may be increased with increased lateral dihedral. increased lateral anhedral. increased longitudinal dihedral. Longitudinal stability is increased if the CG is forward of the CP. Thrust acts on a line below the total drag. CP moves forward of the CG. Directional stability is about the lateral axis. longitudinal axis. normal axis. Lateral stability is about the longitudinal axis. normal axis. vertical axis. Longitudinal stability is provided by the horizontal stabilizer. vertical stabilizer. mainplane. If the aircraft turns and side-slips the sweepback of the wing will correct the sideslip. the keel surface will correct the sideslip. the dihedral of the wing will correct the sideslip. An aircraft disturbed from its normal flight path, and automatically returns to that normal flight path, without any action on the part of the pilot is known as aircraft stall. aircraft instability. aircraft stability. The fin gives stability about which axis? Longitudinal axis. Lateral axis. Normal axis. If the nose of the aircraft is rotated about its lateral axis, what is its directional movement? Rolling or banking to the left or right. Turning to the left or right. Climbing or diving. The function of an aircraft fin is to provide directional control. is to provide straight airflow across the rudder. is to provide stability about the normal axis. Movement of an aircraft about its normal axis is rolling. is yawing. is pitching. If, after a disturbance, an aeroplane initially returns to its equilibrium state it has neutral stability. it has static stability and may be dynamically stable. it is neutrally unstable. Stability of an aircraft is the tendency of the aircraft to return to its original trimmed position after having been displaced. the tendency of the aircraft to stall at low airspeed. the ability of the aircraft to rotate about an axis. The three axes concerned with stability of an aircraft have normal axis through C of G. Lateral axis - wing tip to wing tip. Longitudinal axis - nose to tail but not through C of G. longitudinal, lateral and normal axis all passing through aircraft centre of gravity. longitudinal axis nose to tail, lateral axis at furthest span point, normal axis through centre of pressure. If an aircraft returns to a position of equilibrium it is said to be positively stable. neutrally stable. negatively stable. The pendulum effect on a high wing aircraft has no effect on lateral stability. increases lateral stability. decreases lateral stability. After a disturbance in pitch, an aircraft continues to oscillate at constant amplitude. It is longitudinally unstable. longitudinally neutrally stable. laterally unstable. On an aircraft with an all-moving tailplane nose up pitch is caused by decreasing tailplane incidence. increasing tailplane incidence. up movement of the trim tab. What gives the aircraft directional stability? Vertical stabiliser. Elevators. Horizontal stabiliser. In flight if the aircraft nose gets an upward gust of wind, what characteristic will have the greatest effect to counteract it? Wing Sweep. Horizontal stabiliser and fuselage length. Position of the centre of pressure relative to the centre of gravity.

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