EASA 66 Module 8 Questions.

Module 8 Exam 1  Aerodynamics 1. On a swept wing wing aircraft if both wing wing tip sections lose lose lift simultaneously the the aircraft will will a) roll b) pitch nose up c) pitch nose down 2. ift on a delta wing aircraft a) increases with an increased angle of incidence !angle of attac") b) decreases with an increase in angle of incidence !angle of attac") c) does not change with a change in angle of incidence !angle of attac") #. On a straight straight wing wing aircraft$ stall commences at the a) root on a high thic"ness ratio wing b) tip on a high thic"ness ratio wing c) tip on a low thic"ness ratio wing %. On a high wing wing aircraft in a turn a) the up&going wing loses lift causing a de &stabilising effect b) the down&going wing gains lift causing a stabilising effect c) the down&going wing loses lift causing a de&stabilising effect '. (or the same angle of attac"$ the lift on a delta delta wing a) is greater than the lift on a high aspect ratio wing b) is lower than the lift on a high aspect ratio wing c) is the same as the lift on a high aspect ratio wing . *he +,A a) is ta"en from the e-uator b) is ta"en from %' degrees latitude c) assumes a standard day . At higher altitudes as altitude increases$ pressure a) decreases at constant rate b) increases exponentially c) decreases exponentially 8. *he thrust&drag couple couple o/ercomes the lift&weight lift&weight couple. 0hat direction of force force is re-uired to be produced by the tail of the aircraft to maintain straight and le/el flight a) upwards b) downwards c) sideways . 0hen the pressure is half of that at sea le/el$ le/el$ what what is the altitude a) 12$333 ft b) 8$333 ft c) 18$333 ft 13. 4uring a turn$ the stalling angle a) increases b) decreases c) remains the same Module 8 Exam 2  Aerodynamics 1

Module 8 Exam #  Aerodynamics 1. At stall$ the wingtip wingtip stagnation point a) mo/es toward the lower surface of the wing b) mo/es toward the upper surface of the wing c) doesn9t mo/e 2. :ow does +A, at the point of stall /ary with with height a) +t is practically constant b) +t increases c) +t decreases #. *he rigging rigging angle of incidence of an ele/ator is is a) the angle between the mean chord line and the hori;ontal in the rigging position b) the angle between the bottom surface of the ele/ator and the hori;ontal in the rigging position c) the angle between the bottom surface of the ele/ator and the longitudinal datum %. 0hat is the lapse rate with regard to to temperature temperature o a) 1.8 6 per 1333 ft b) 1.8o( per 1333 ft c) %o6 per 1333 ft '. 0hat happens to to load factor as you decrease turn radius a) +t increases b) +t decreases c) +t remains constant .

+f you steepen the angle angle of a ban"ed turn without increasing increasing airspeed or angle of attac"$ what will will the aircraft do a) +t will remain at the same height b) +t will sideslip with attendant loss of height c) +t will stall

. An aircraft aircraft wing wing tends to stall first at a) the tip due to a higher ratio thic"nesselati/e humidity b) 4ew point c) Absolute humidity . An aspect ratio of 8 means a) the span is 8 times the mean chord b) the mean chord is 8 times the span c) the area is 8 times the span . +n a turn$ if your centrifugal force is greater than the hori;ontal component of lift a) ou are slipping b) ou are s"idding c) ou are in a coordinated turn 8. 0hich will weigh the least a) 8 parts of dry air and 2 parts of water /apour b) #' parts of dry air and ' parts of water /apour c) '3 parts of dry air and '3 parts of water /apour . A high aspect ratio wing a) is stiffer than a low aspect ratio wing b) has less induced drag than a low aspect ratio wing c) has a higher stall angle than a low aspect ratio wing 13. *he thrust line of an engine may be set slightly to the right on aircraft manufacture to a) counteract the turning tendency due to propeller tor-ue b) assist in a climbing turn c) pre/ent hori;ontal o scillation

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Module 8 Exam 2'  Aerodynamics 1. +nduced downwash a) reduces the effecti/e angle of attac" of the wing b) increases the effecti/e angle of attac" of the wing c) has no effect on the angle of attac" of the wing 2. 4uring a turn$ the stalling angle a) increases b) decreases c) remains the same #.

0hich is the ratio of the water /apour actually present in the atmosphere to the amount that would be present if the air were saturated at the pre/ailing temperature and pressure a) Absolute humidity b) >elati/e humidity c) 4ew point

%. A straight rectangular wing$ without any twist$ will a) ha/e greater angle of attac" at the tip b) ha/e the same angle of attac" at all points along the span c) ha/e less angle of attac" at the tip '. 7i/en 2 wings$ the first with a span of 12m and a chord of 2 m. *he second has a span of m and a chord of 1m. :ow do their Aspect >atios compare a) *he first is higher b) *he second is higher c) *hey are the same . *he 6 of 7 mo/es in flight. *he most li"ely cause of this is a) mo/ement of passengers b) mo/ement of cargo c) consumption of fuel and oils . *he speed of sound in the atmosphere a) /aries according to the fre-uency of the sound b) changes with a change in temperature c) changes with a change in pressure 8. A straight rectangular wing$ without any twist$ will a) stall first at the tip b) stall first at the root c) stall e-ually along the span of the wing . 0hat is sea le/el pressure a) 131#.2 mb b) 1312.# mb c) 13#2.2 mb 13. 0hich atmospheric conditions will cause the true landing speed of an aircraft to be the greatest a) ow temperature with low humidity b) :igh temperature with low humidity c) :igh temperature with high h umidity

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Module 8 Exam 2  Aerodynamics 1. +n flight if your aircraft nose gets an upward gust of wind$ what characteristic will ha/e the greatest effect to counteract it a) :ori;ontal stabiliser and fuselage length b) 0ing ,weep c) 5osition of the centre of pressure relati/e to the centre of gra/ity 2. 0hen the weight of an aircraft increases$ the minimum drag speed a) decreases b) increases c) remains the same #. 0hich statement concerning heat andight c) either %. *he trailing /ortex on a pointed wing !taper ratio C 3) is a) at the root b) at the tip c) e-ually all along the wing span '. A high wing aircraft will be more a) laterally stable than a low wing aircraft b) longitudinally stable than a low wing aircraft c) directionally stable than a low wing aircraft . A wing with a /ery high aspect ratio !in comparison with a low aspect ratio wing) will ha/e a) increased drag at high angles of attac" b) a high stall speed c) poor control -ualities at low airspeeds . *he lift cur/e for a delta wing is a) more steep than that of a high aspect ratio wing b) less steep than that of a high aspect ratio wing c) the same as that of a high aspect ratio wing 8.

After an aircraft has been disturbed from its straight and le/el flight$ it returns to its original attitude with a small amount of decreasing oscillation. *he aircraft is a) statically stable but dynamically unstable b) statically unstable but dynamically stable c) statically stable and dynamically stable

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An increase in the speed at which an aerofoil passes through the air increases lift because a) the increased speed of the airflow creates a greater pressure differential between the upper and lower surfaces. b) the increased speed of the airflow creates a lesser pressure differential between the upper and lower surfaces. c) the increased /elocity of the relati/e wind increases the angle of attac"

13. A delta wing has a) a higher stall angle than a straight wing b) a lower stall angle than a straight wing c) the same stall angle than a straight wing

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Module 8 Exam 2  Aerodynamics 1. *he iftams :orn @ortex on a forward swept wing will be a) the same as a rearward swept wing b) more than a rearward swept wing c) less than a rearward swept wing

. 0hen maintaining le/el flight an increase in speed will a) cause the 6 of 5 to mo/e aft b) cause the 6 of 5 to mo/e forward c) ha/e no affect on the position of the 6 of 5

13. (or a cambered wing section the ;ero lift angle of attac" will be a) ;ero b) % degrees c) negati/e

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Module 8 Exam #1  Aerodynamics 1. 4ensity changes with altitude at a rate a) of 2"gemains the same 2. *he boundary layer o/er an aerofoil is a) a layer of air close to the aerofoil that is stationary b) a layer of air close to the aerofoil which is mo/ing at a /elocity less than free stream air c) a layer of turbulent air close to the aerofoil which is mo/ing at a /elocity less than free stream air #. On a swept wing aircraft$ the fineness ratio of an aerofoil is a) highest at the root b) highest at the tip c) e-ual throughout the span %. +A, for a stall will a) increase with altitude b) decrease with altitude c) roughly remain the same for all altitude '. +f the radius of a turn is reduced the load factor will a) increase b) decrease c) remain the same . ,treamlining will reduce a) form drag b) induced drag c) s"in friction drag . +f an aircraft has a gross weight of #333 "g and is then sub=ected to a total weight of 333 "g the load factor will be a) 27 b) #7 c) 7 8. A constant rate of climb is determined by a) weight b) wind speed c) excess engine power . +ce formed on the leading edge will cause the aircraft to a) stall at the same stall speed and AoA b) stall at a lower speed c) stall at a higher speed 13. 0ith an aircraft in ban"$ the upper wing produces more drag. *o compensate a) the rudder is operated b) when ban" angle is achie/ed then the ailerons are operated in the opposite direction to cause the opposite effect c) angle of attac" is increased

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Module 8 Exam #%  Aerodynamics 1. +f both wings lose lift the aircraft a) pitches nose up b) pitches nose down c) glides on a hori;ontal plane

2. Jnder what conditions will an aircraft create best lift a) 6old dry day at 233 ft b) :ot damp day at 1233 ft c) 6old wet day at 1233 ft

#. +f there is an increase of density$ what effect would there be in aerodynamic dampening a) one b) 4ecreased c) +ncreased

%. As Mach number increases$ what is the effect on boundary layer a) ?ecomes more turbulent b) ?ecomes less turbulent c) 4ecreases in thic"ness

'. 0hen a slat is retracted it mo/es a) towards the upper leading edge of the wing b) towards the lower leading edge of the wing c) towards the center of the leading edge of the wing

. +n a turn the up&going wing causes a a) de&stabilising effect due to increased AoA b) de&stabilising effect due to decreased AoA c) stabilising effect due to decreased AoA

. *he stagnation point consists of a) dynamic and static air pressure b) static air pressure c) dynamic air pressure

8. 4uring a glide the following forces act on an aircraft a) lift$ weight$ thrust b) lift$ drag$ weight c) lift and weight only

. awing is a rotation around a) the normal axis obtained by the ele/ator b) the lateral axis obtained by the rudder c) the normal axis obtained by the rudder

13. +f an aileron is mo/ed downward a) the stalling angle of that wing is increased b) the stalling angle of that wing is decreased c) the stalling angle is not affected but the stalling speed is decreased

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Module 8 Exam #'  Aerodynamics 1. +f the wing loading of an aircraft were reduced the stalling speed would a) increase b) decrease c) not be affected

2. 4ensity changes with altitude at a rate a) of 2 "g