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TEST BORRADO, QUIZÁS LE INTERESE: 3272-8 Aero (8.10)

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Título del Test: 3272-8 Aero (8.10) Descripción: 3272-8 Aero (8.10) Autor: Atom OTROS TESTS DEL AUTOR Fecha de Creación: 14/10/2024 Categoría: Otros Número Preguntas: 52

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To correct dutch roll you must damp oscillation around the longitudinal axis. the lateral axis. the vertical axis. An elevator trim tab is used to counteract propeller torque. prevent the control surface from stalling the airflow. reduce control column forces on the pilot. A high wing aircraft will be more laterally stable than a low wing aircraft. longitudinally stable than a low wing aircraft. directionally stable than a low wing aircraft. After an aircraft has been disturbed from its straight and level flight, it returns to its original attitude with a small amount of decreasing oscillation. The aircraft is statically stable but dynamically unstable. statically unstable but dynamically stable. statically stable and dynamically stable. If there is an increase of density, what effect would there be in aerodynamic dampening? Decreased. Increased. None. Yawing is a rotation around the lateral axis obtained by the rudder. the normal axis obtained by the rudder. the normal axis obtained by the elevator. Lateral stability is reduced by increasing dihedral. sweepback. anhedral. Azimuth stability is dependent on dihedral. keel and fin. tailplane. Sweepback of the wings will increase lateral stability at high speeds only. not affect lateral stability. increase lateral stability at all speeds. If you have an aircraft that is more laterally stable then directionally stable it will tend to bank. slip. skid. A centre of gravity position close to its aft limit will cause the aircraft to pitch nose down and increase its longitudinal stability. pitch nose up and decrease its longitudinal stability. pitch nose up and increase its longitudinal stability. A sharply swept wing will promote excessive lateral instability. excessive longitudinal stability. excessive lateral stability. Which control surfaces provide lateral control , also longitudinal control and stability? Ruddervators. Tailerons. Flapperons. 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. Yaw dampers are designed to prevent dutch roll. assist the pilot to move the rudder. reduce the effect of crabbing due to cross winds. Tuck under occurs when a shock stall occurs on the outboard portion of swept wing. a shock stall warning occurs on the inboard position of a straight wing. the aircraft reaches Mcrit. The lateral axis is a straight line through the CG at right angles to the longitudinal and lateral axis. a straight line through the CG from nose to tail. a straight line through the CG parallel to a line joining the wingtips. The main factors which affect longitudinal stability are design of the fuselage and position of the CG. design of the mainplane and position of the CG. design of the tailplane and position of the CG. A yawing motion provides what kind of Stability? Directional. Lateral. Longitudinal. Where would you find the normal axis? Through C of G at right angles to longitudinal and lateral axis. Vertically through CofP. In line with the wing tips through C of G. When a aircraft is in a slideslip and is yawing the the fin will correct the yawing motion. the effective keel area will make the ac yaw further into the direction of the sideslip. the dihedral will prevent the yaw motion. As a consequence of the C of G being close to its aft limit the stick forces to manoeuvre longitudinally will be low due to low stability. the stick forces will be high in fore and aft pitch, due to the high longitudinal stability. the stick forces when pitching the nose down will be very high. With the C of G on its forward limit the change in control loading is dependant on the position of the CofP. control loading decreases. control loading increases. An undercarriage leg in flight produces 3 lbs of drag at 100kts. If speed is increased to 200kts the drag would be 12 lbs. 6 lbs. 9 lbs. A stall warning device must be set to operate at a speed just above stalling speed. at a speed just below stalling speed. at the stalling speed. In cruise the weight of an aeroplane is decreasing as fuel is used. A stall would occur at a lower speed. at the same speed. at a higher speed. As height increases, with angle of attack and speed constant lift will remain constant. lift Increases. lift decreases. On a swept wing aircraft if both wing tip sections lose lift simultaneously the aircraft will roll. pitch nose up. pitch nose down. Lift on a delta wing aircraft increases with an increased angle of incidence (angle of attack). decreases with an increase in angle of incidence (angle of attack). does not change with a change in angle of incidence (angle of attack). On a straight wing aircraft, stall commences at the root on a high thickness ratio wing. tip on a high thickness ratio wing. tip on a low thickness ratio wing. On a high wing aircraft in a turn the up-going wing loses lift causing a de-stabilizing effect. the down-going wing gains lift causing a stabilizing effect. the down-going wing loses lift causing a de-stabilizing effect. For the same angle of attack, the lift on a delta wing is greater than the lift on a high aspect ratio wing. is lower than the lift on a high aspect ratio wing. is the same as the lift on a high aspect ratio wing. The ISA? is taken from the equator. is taken from 45 degrees latitude. assumes a standard day. The thrust-drag couple overcomes the lift-weight couple. What direction of force is required to be produced by the tail of the aircraft to maintain straight and level flight upwards. downwards. sideways. During a turn, the stalling angle increases. decreases. remains the same. The C of G moves in flight. The most likely cause of this is movement of passengers. movement of the centre of pressure. consumption of fuel and oils. The C of P is the point where all the forces on an aircraft act. the three axis of rotation meet. the lift can be said to act. The three axis of an aircraft act through the C of G. C of P. stagnation point. When the weight of an aircraft increases, the minimum drag speed decreases. increases. remains the same. An aircraft will have less gliding distance if it has more payload. more gliding distance if it has more payload. the same gliding distance if it has more payload. When an aircraft experiences induced drag air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root. air flows under the wing spanwise towards the root and on top of the wing spanwise towards the tip. Neither a) or b) since induced drag does not caused by spanwise flow. What happens to load factor as you decrease turn radius? It increases. It decreases. It remains constant. If you steepen the angle of a banked turn without increasing airspeed or angle of attack, what will the aircraft do? It will remain at the same height. It will sideslip with attendant loss of height. It will stall. An aircraft wing tends to stall first at the tip due to a higher ratio thickness/chord. the tip due to a lower ratio thickness/chord. the root due to a higher ratio thickness/chord. To stop aircraft decreasing in height during a sideslip, the pilot can advance the throttle. pull back on the control column. adjust the rudder position. What control surface movements will make an aircraft fitted with ruddervators yaw to the left? Left ruddervator lowered, right ruddervator raised. Right ruddervator lowered, left ruddervator raised. Both ruddervators raised. When a leading edge slat opens, there is a gap between the slat and the wing. This is to allow it to retract back into the wing. to allow air through to re-energize the boundary layer on top of the wing. to keep the area of the wing the same. If the wing tips stall before the root on a swept wing aircraft, the aircraft will roll. pitch nose up. pitch nose down. The thrust-drag couple overcomes the lift-weight couple. What direction of force is required to be produced by the tail of the aircraft to maintain straight and level flight? Upwards. Downwards. Sideways. The vertical fin of a single engined aircraft is parallel with both the longitudinal axis and vertical axis. parallel with the longitudinal axis but not the vertical axis. parallel with the vertical axis but not the longitudinal axis. Aircraft flying in the transonic range most often utilize sweptback wings. advanced supercritical airfoils. high wings. Which type of flap changes the area of the wing? Fowler. Split. Slotted.

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