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TEST BORRADO, QUIZÁS LE INTERESE: 3272-11 Sys (1.1)

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Título del Test: 3272-11 Sys (1.1) Descripción: 3272-11 Sys (1.1) Autor: Chespirito OTROS TESTS DEL AUTOR Fecha de Creación: 21/09/2024 Categoría: Letras Número Preguntas: 90

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Windscreen heating is supplied from frequency wild generator, via a rectifier. frequency wild generator, direct to the windscreen. DC generator, via a transformer. The stall speed does not depend on weight. increases with an increased weight. decreases with an increased weight. A wing has a span of 50 feet and an area of 200 square feet. Its mean chord would be 4 feet. 10 feet 7.5 feet. Wing spoilers, when used asymmetrically, are associated with ailerons. elevators. rudder. As a subsonic aircraft speeds-up, its Centre of Pressure is unaffected. moves forward. moves aft. Slats are used to ensure the boundary layer does not separate from the wing surface too soon. decrease the stalling angle. change the wing camber. Deploying a secondary flight control surface will not affect the angle of attack . decrease the angle of attack of the aerofoil. increase the angle of attack of the aerofoil . If an aircraft is yawing to the left, where would you position the trim tab on the rudder to correct? To the right. To the centre. To the left. A plain flap when retracted forms the lower surface of the wing. when extended provides a slot between the wing and the flap. when extended rotates on a simple hinge as if to bend the trailing edge of the wing down. If an aircraft is flying with a left wing low, where would you move the left aileron trim tab to correct? Up Down Moving the aileron trim tab will not correct the situation. When a leading edge flap is fully extended, what is the slot in the wing for? To allow the flap to retract into it when it retracts. To increase the lift. To re-energise the boundary layer. Sweepback on the wing will cause stall to occur at lower angles of attack reduce tendency to tip stall. increase tendency to tip stall. With respect to differential aileron control, which of the following is true? The up -going and down - going ailerons both deflect to the same angle. The up -going aileron moves through a smaller angle than the down-going aileron. The down-going aileron moves through a smaller angle than the up-going aileron. The aeroplane fin is of symmetrical aerofoil section and will therefore provide a side -load only if a suitable angle of attack develops due to yaw. only when the rudder is moved. if a suitable angle of attack develops due either yaw or rudder movement. An aircraft left wing is flying low. The aileron trimmer control to the left aileron trim tab in the cockpit would be moved -down causing the left aileron to move down. moved -up causing the left aileron to move up. moved -up causing the left aileron to move down. What is true regarding deployment of Slats / Krueger flaps? Krueger flaps increase the critical angle of attack, Slats do not. Slats form a slot, Krueger flaps do not. Slats increase the critical angle of attack, Krue ger flaps do not. On a swept back wing, in which of the following locations would Krueger Flaps be fitted? Outboard leading edge. Inboard leading edge. The trailing edge. An aeroplane performs a straight and level horizontal flight at the same angle of attack at two different altitudes: (all other factors of importance being constant, assume ISA conditions and no compressibility effects) the TAS at the higher altitude is higher. the TAS at the higher altitude is lower. the TAS at both altitudes is the same. Extending the flaps while maintaining a constant angle of attack (all other factors constant) the aircraft will climb. the aircraft will yaw. the aircraft will sink suddenly. What pitching moment will be generated when Fowler flaps are deployed on an aircraft with a high mounted (T - tail) tailplane? An aircraft nose down pitching moment. The nose up pitching moment will be balanced by the nose down pitching moment. An aircraft nose up pitching moment. An increase in aspect ratio will cause VbaseMD to be increased. cause induced drag to increase. cause VbaseMD to be reduced. Geometric washout means that the tip of the wing has more angle of attack than the root. there is an airflow along the wing that keeps it clean. the tip of the wing has l ess angle of attack than the root. The purpose of a slot in a wing is to speed up the airflow and increase lift. provide housing for the slat. act as venturi, accelerate the air and re - energise boundary layer. Large flap deployment has no effect on spanwise flow. causes increased spanwise flow towards tips on wing lower surface. causes increased spanwise flow towards tips on wing upper surface. How do vortex generators work? Reduce the adverse pressure gradient. Take energy from free stream and introduce it into the boundary layer. Re-direct slantwise flow. Winglets decrease the static lateral stability. create an elliptical lift distribution. decrease the induced drag. Which part of the wing of a swept - wing aircraft stalls first? Both stall together. Root stalls first. Tip stalls first. A function of vortex generators in the transonic regime is to reduce boundary layer separation drag when shockwaves form. prevent the rearward shift of CP on swept wing stalls. reduce wing root compres sion effects. During flight, an aircraft is yawing to the right. The aircraft would have a tendency to fly right wing low. left wing low. nose up. During acceleration in level flight the transition point on the wing moves forward. the lift coeffici ent reduces. the wing stagnation point moves aft . As altitude increases, the equivalent airspeed at which an aeroplane stalls in a particular configuration will remain the same regardless of altitude. remain equal to the calibrated airspeed. decrease as the true airspeed decreases. With a drop in ambient temperature, an aircraft service ceiling will not be affected. lower. rise. When an aeroplane is flying at an airspeed which is 1.3 times its basic stalling speed, the coefficient of lift as a percentage of the maximum lift coefficient (CLmax) would be 59%. 130%. 77% . To maintain level flight, if the angle of attack is increased the speed must be increased in the same ratio as the lift/drag ratio decreases. reduced. increased. Flap selec tion at constant IAS in straight and level flight will increase the maximum lift coefficient (CLmax) and the drag. lift and the drag. lift coefficient and the drag. In straight and level flight, if airspeed ... the angle of attack ... and the incidence angle... increases; decreases; decreases. increases; increases; decreases. decreases; increases; remains constant. What must happen to the CL when flaps are deployed while maintaining a constant IAS in straight and level flight? Remain constant. Decrease. Increase. If VS is 100 kt in straight and level flight, during a 45 bank turn VS will be 119 kts. 100 kts. 140 kts. What is the effect on TAS if altitude is increased to 35,000 ft while flying at a constant Mach number? Remain the same. Increase then remain constant. Decrease. If IAS is doubled, by which of the following factors should the original CL be multiplied to maintain level flight? 4.0 0.5 0.25. When an aircraft is in a steady climb, how will the wing stalling angle be affected? The stalling angle will remain the same, regardless of altitude. The stalling angle will in crease with increasing altitude. The stalling angle will reduce with increasing altitude. The centre of pressure is in its most forward position when t he angle of attack is equal to the stalling angle of attack. when the angle of attack exceeds the stalling angle of attack. when the angle of attack is smaller than the stalling angle of attack. The angle of attack at which an aircraft stalls increases with an increase in gross weight. remains constant regardless of gross weight. varies with gross weight and density altitude. The following factors increase stall speed: A higher weight, selecting a higher flap setting, a forward c.g. shift. An increase in load factor, a forward c.g. shift, decrease in thrust. A lower weight, decreasing bank angle, a smaller flap setting. Stall speed in a turn is proportional to weight. the square root of the load factor. lift. An aeroplane has a stalling speed of 100 kt in a steady level flight. When the aeroplane is flying a level turn with a load factor of 1.5, the stalling speed is 122 kt. 141 kt. 82 kt. A wing stalling angle is decreased in a turn. unaffected by a turn. increased in a turn. What effect does an increased load have on an aircraft? The aircraft will stall at a higher speed. The aircraft will suffer immediate structural failure. The aircraft will have a tendency to roll and yaw. The aircraft will stall at a higher speed. Which stall has the greatest angle of attack? Deep stall. Low speed stall. High speed stall (shock stall). A jet aeroplane cruises buffet free at high constant altitude in significant turbulence. Which type of stall can occur if this aeroplane decelerates? Shock stall. Low speed stall. Accelerated stall. On a swept wing aeroplane at low airspeed, the pitch -up phenomenon is caused by wingtip stall. never occurs, since a swept wing is a remedy to pitch up. is caused by extension of trailing edge lift augmentation devices. Which of the following statements about stall speed is correct? Increasing the angle of sweep of the wing will decrease the stall speed. Use of a T-tail will decrease the stall speed. Decreasing the angle of sweep of the wing will decrease the stall speed. How are the wing stalling angle and the lift coefficient affected when altitude increases and EAS is held constant? The lift coefficient remains constant and the wing stalling angle will reduce. The lift coefficient and the wing stalling angle both decrease. The lift coefficient and the wing stalling angle both remain constant. Increase of wing loading will decrease the minimum gliding angle. increase the stall speed. decrease take off speeds. The most common stall sensing devices are normally located on the upper surface of the wing. at or near the wing leading edge. on the lower surface of the wing. If angle of attack is increased beyond th e critical angle of attack, the lift coefficient ... and the stagnation point moves... decreases; rearward increases; rearward decreases; forward. In a turn, the wing stalling angle remains unchanged. decreases. increases. As the angle of attack of a wing is increased, the centre of pressure will reach its most forward position on the wing just before the wing stalls. when the aircraft is stalling. after stall recovery. Which kind of boundary layer has the strongest change in velocity close to the surface? Turbulent boundary layer. No difference. Laminar boundary layer. One disadvantage of the swept back wing is it is stalling characteristics. At the stall tip stall will occur first, which produces a nose -down moment. tip stall will occur first, which produces a pitch -up moment. wing root stall will occur first, which produces a rolling moment. Which of the following aircraft designs would be most prone to super stall? T-tail. Swept forward wing. Swept back wing. The stall speed in a 60° banked turn increases by the following factor: 1. 1.41. 2.00. The speed range between high and low speed buffet increases during descent at a constant IAS. decreases during a descent at a constant Mach number. increases during climb. The boundary layer of a wing is caused by a layer on the wing in which the stream velocity is lower than the free stream velocity, due to friction. suction at the upper wing side. a turbulent stream pattern around the wing. The stalling speed in IAS will change according to the following factors? May increase with altitude, especially high altitude, will increase during icing conditions and will increase when the c.g. moves forward. Will increase in a turn, higher temperature and will in crease when the c.g. moves aft. Will increase with increased load factor, more flaps and increased bank angle in a turn. The pitch -up effect of an aeroplane with swept wing in a stall is due to the forward movement of the centre of gravity. wing root stalling first. wing tip stalling first. When an aircraft with a typical aerofoil is in level flight at low speed and high angle of attack, the normal axis is horizontal from side to side. nearly vertical vertical. An aeroplane has a stall speed of 78 KCAS at its gross weight of 6.850 lbs. What is the stall speed when the weight is 5.000 lbs? 67 KCAS 91 KCAS 78 KCAS. What causes a swept wing aircraft to pitch-up at the stall? Rearward movement of the CP. Spanwise flow. Separated airflow a t the root. Load factors has the following meaning: The ratio of a specified load to the weight of the aircraft, the former being expressed in terms of aerodynamic forces, inertia forces and ground reactions. The ratio of a specified load to the mass o f the aircraft, the former being expressed in terms of aerodynamic forces, inertia forces and ground reactions. The ratio of a specified load to the mass or the aircraft the former being expressed in terms of aerodynamic and inertia forces. When all other factors of importance are constant, the stall speed increases when spoilers are retracted. pulling out of a dive. weight decreases. Which of the following is the correct order of configuration to give an increasing critical angle of attack? Trailing edge flaps extended, clean wing, slats extended. Slats extended, clean wing, trailing edge flaps extended. Clean wing, trailing edge flaps extended, slats extended. What is the percentage increase in stall speed in a 45° bank turn 19%. 10%. 45%. When an aircraft wing stalls a wing which is not swept back will stall from the root and the CP will move forwards. a swept back wing will stall from the tip and the CP will move forward. a swept back wing will stall from the root and the CP will move aft . At the same weight, with the CG at its forward limit VbaseS is higher, the stalling angle is unchanged. VbaseS is lower, the stalling angle is unchanged. VbaseS is higher, the stalling angle is greater. Two identical aeroplanes A and B are flying horizontal steady turns. Further data is: A: W=1500 kg Bank= 20° TAS= 130 kt, B: W= 1500 kg Bank= 20° TAS= 200 kt. Which of the following statements is correct? The rate of turn A is larger than the rate of turn B. The turn radius A is larger than the turn radius B. The load factor A is larger than the load factor B. Which of the following situations leads to a decreasing stall speed (IAS)? Increasing air density. Increasing load factor. Decreasing weight. The purpose of a fixed spoiler on the leading edge of a wing at the root is to 10 %. 50%. 40%. The critical angle of attack increases if the CG is moved forward. changes with an increase in gross weight. remains unchanged regardless of gross weight . An aeroplane has been loaded in such a manner that the centre of gravity is located behind the aft centre of gravity limit. One undesirable flight characteristic a pilot might experience with this aeroplane would be difficulty in recovering from a stalled condition. a longer takeoff run. stalling at higher -than -normal airspeed. V[base=so] is defined as the stalling speed or minimum takeoff safety speed. stalling speed or minimum steady flight speed in a specified configuration. stalling speed or minimum steady flight speed in the landing configuration. The stalling speed in IAS will change according to the following factors: Decrease in a forward c.g. location, higher altitude and due to the slip stream from a propeller on an engine located forward of the wing. Increase with increased load factor, icing conditions and an aft c.g. location. Increase during turn, increased mass and forward c.g. location. With the centre of gravity on the forward limit, the stalling speed would be lower than with the centre of gravity on the aft limit. the same as with the centre of gravity on the aft limit. higher than with the centre of gravity on the aft limit. The following takes place at the transition point on a wing: The airflow separates completely from the wing surface. The boundary layer makes the transition from laminar flow to the turbulent boundary layer. The total dynamic and static pressure comes to a standstill. A low wing loading (aircraft weight has been reduced) decreases stalling speed and la nding speed. increases take -off run, stalling speed and landing speed. increases stalling speed. Stalling speed in a 15° bank level turn is 60kt. The stalling speed in a 45° bank level turn will be 60 kts. 70 kts. 50 kts. How does stalling speed (IAS) vary with altitude? It remains constant at lower altitudes but decreases at higher altitudes due to compressibility effects. It remains constant. It increases with increasing altitude, because the density decreases. Extending a leading edge slat will have what effect on the angle of attack of a wing? Decrease the angle of attack. No effect on angle of attack. Increase the angle of attack. As the centre of gravity is changed, recovery from a stall becomes progressively becomes progressively more difficult as the centre of gravity moves aft. is unaffected by centre of gravity position. becomes progressively more difficult as the centre of gravity moves forward. To ensure that a wing stalls at the root first, stall we dges are installed at the wing trailing edge at the wing root. installed on the wing leading edge at the wing root. installed on the wing leading edge at the wing tip.

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