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EXP AERODYNAMICS

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EXP AERODYNAMICS

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  1. 140)The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. Increase in angle of attack of 1 degree will increase CL by 0.079. A vertical up gust instantly changes the angle of attack by 2 degrees. The load factor will be : A1.9 B1.45 C0.9 D0.45

  2. 141) Which aeroplane behaviour will be corrected by a yaw damper ? • A Spiral dive. • B Buffeting. • C Dutch roll. • DTuck under.

  3. 142) The aft movement of the centre of pressure during the acceleration through the transonic flight regime will: • Adecrease the static lateral stability. • B increase the static longitudinal stability. • Cdecrease the longitudinal stability. • D increase the static lateral stability.

  4. 143) The relative thickness of an aerofoil is expressed in: • A camber. • Bmeters. • Cdegrees cross section tail angle. • D% chord.

  5. 144)The frontal area of a body, placed in a certain airstream is increased by a factor 3. The shape will not alter. The aerodynamic drag will increase with a factor : • A 1.5. • B 3. • C 9. • D 6.

  6. 145) (For this question use annex 081-6271A) The high lift device shown in the figure is a • A Slat • B Fowler flap • C Slotted flap • D Krueger flap

  7. 146) One disadvantage of the swept back wing is it's stalling characteristics. At the stall : • Awing root stall will occur first, which produces a rolling moment • B tip stall will occur first, which produces a nose-down moment • C leading edge stall will occur first, which produces a nose down moment • D tip stall will occur first, which produces a pitch-up moment.

  8. 147) Shock induced separation results in • Adecreasing lift. • Bconstant lift. • C increasing lift. • Ddecreasing drag.

  9. 148) (For this question use annex 081-6249A) Which line represents the total drag line of an aeroplane? • A Line d • B Line c • C Line a • D Line b

  10. 149) In what way is the longitudinal stability affected by the degree of positive camber of the aerofoil? • A Positive, because the centre of pressure shifts rearward at increasing angle of attack. • BNegative, because the lift vector rotates forward at increasing angle of attack. • CPositive, because the lift vector rotates backward at increasing angle of attack. • DNo effect, because camber of the aerofoil produces a constant pitch down moment coefficient, independent of angle of attack.

  11. 150) (For this question use annex 081-1331A) An A 310 aeroplane weighing 100 tons is turning at FL 350 at constant altitude with a bank of 50 degrees. Its flight Mach range between low-speed buffeting and high speed buffeting goes from: • AM= 0.72 to M higher than 0.84 • B M= 0.65 to M higher than 0.84 • C M= 0.74 to M= 0.84 • D M= 0.69 to M higher than 0.84

  12. 151) The critical Mach Number of an aeroplane can be increased by: • Asweep back of the wings. • B vortex generators. • C control deflection • D dihedral of the wings.

  13. 152) If an aeroplane flies in the ground effect • A the lift is increased and the drag is decreased. • Bthe effective angle of attack is decreased. • C the induced angle of attack is increased. • D drag and lift are reduced.

  14. 153) Flap selection at constant IAS in straight and level flight will increase the : • Alift and the drag. • B maximum lift coefficient (CL max) and the drag. • C lift coefficient and the drag. • D stall speed.

  15. 154) Which of these definitions of propeller parameters is correct? • A Propeller angle of attack = angle between blade chord line and propeller vertical plane • B Critical tip velocity = propeller speed at which risk of flow separation at some parts of propeller blade occurs. • C geometric propeller pitch = the theoretical distance a propeller blade element is travelling in forward direction in one propeller revolution • DBlade angle = angle between blade chord line and propeller axis

  16. 155) Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is: • A 1.30 VS. • B 1.12 VS. • Cgreater than VS. • D 1.20 VS.

  17. 156) Which one of the following systems suppresses the tendency to "Dutch roll"? • ARudder limiter. • BYaw damper. • CRoll spoilers. • DSpoiler mixer.

  18. 157) Bernoulli's equation can be written as : (pt = total pressure, ps = static pressure, q = dynamic pressure) • Apt= q - ps • Bpt- q = ps • C pt = ps - q • D pt + ps = q

  19. 158) Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)? • A a=F. m • B F=m / a • C F=m. a • D m=F.a

  20. 159) The high speed buffet is induced by • A boundary layer separation due to shock waves. • B boundary layer control. • C expansion waves on the wing upper side. • D a shift of the centre of gravity.

  21. 160) "A line connecting the leading- and trailing edge midway between the upper and lower surface of a aerofoil". This definition is applicable for : • A the mean aerodynamic chord line • B the upper camber line • C the camber line • D the chord line

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