#1. In a stationary subsonic streamline flow pattern, if the streamlines converge, in this part of the pattern, the static pressure (I) will …and the velocity (II) will … :
#2. The units of the density of the air (I) and the force (II) are:
#3. The units of wing loading (I) W / S and (II) dynamic pressure q are:
#4. Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
#5. The static pressure is acting:
#6. Consider a certain stream line tube. The velocity of the stream in the tube is V. An increase of temperature of the stream at constant value of V will:
#7. Which one of the following statements about Bernoulli’s theorem is correct?
#8. In a two-dimensional flow pattern, where the streamlines converge the static pressure will :
#9. Bernoulli’s equation can be written as:(pt= total pressure, ps = static pressure and q=dynamic pressure)
#10. The unit of density is:
#11. The unit of measurement of pressure is:
#12. The total pressure is:
#13. The (subsonic) static pressure:
#14. The true airspeed (TAS) is:
#15. The difference between IAS and TAS will:
#16. What is the unit of measurement for power ?
#17. The following unit of measurement: kgm/s² is expressed in the SI-system as :
#18. The continuity equation states: If the area of a tube is increasing, the speed of the subsonic and incompressible flow inside is
#19. If the continuity equation is applicable, what will happen to the air density (rho) if the cross sectional area of a tube changes ? (low speed, subsonic and incompressible flow)
#20. Bernoulli’s equation can be written as :(pt = total pressure, ps = static pressure, q = dynamic pressure)
#21. Which of the following statements, about a venturi in a sub-sonic airflow are correct?1. the dynamic pressure in the undisturbed flow and in the throat are equal.2. the total pressure in the undisturbed flow and in the throat are equal.
#22. The angle between the airflow (relative wind) and the chord line of an aerofoil is:
#23. Considering a positive cambered aerofoil, the pitch moment when Cl=0 is:
#24. On a symmetrical aerofoil, the pitch moment for which Cl=0 is:
#25. Drag is in the direction of – and lift is perpendicular to the:
#26. The correct drag formula is:
#27. Lift and drag on an aerofoil are vertical respectively parallel to the
#28. The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
#29. The angle of attack of a two dimensional wing section is the angle between :
#30. The angle between the aeroplane longitudinal axis and the chord line is the:
#31. The term angle of attack in a two dimensional flow is defined as:
#32. Which statement is correct about the Cl and angle of attack?
#33. The relative thickness of an aerofoil is expressed in:
#34. “”A line connecting the leading- and trailing edge midway between the upper and lower surface of a aerofoil””. This definition is applicable for :
#35. The angle of attack of a wing profile is defined as the angle between :
#36. The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
#37. The aspect ratio of the wing:
#38. Dihedral of the wing is:
#39. Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur ?
#40. With increasing angle of attack, the stagnation point will move (I) …and the point of lowest pressure will move (II) …Respectively (I) and (II) are:
#41. Which statement is correct?
#42. The point, where the aerodynamic lift acts on a wing is:
#43. The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:
#44. Lift is generated when:
#45. The lift force, acting on an aerofoil :
#46. On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane) :
#47. The Cl – alpha curve of a positive cambered aerofoil intersects with the vertical axis of the Cl – alpha graph:
#48. The lift formula is:
#49. The terms “”q”” and “”S”” in the lift formula are:
#50. The critical angle of attack:
#51. 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)
#52. The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:
#53. A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor :
#54. A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor :
#55. Comparing the lift coefficient and drag coefficient at normal angle of attack:
#56. The polar curve of an aerofoil is a graphic relation between :
#57. The lift- and drag forces, acting on a wing cross section:
#58. The aerofoil polar is:
#59. 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 :
#60. Increasing dynamic (kinetic) pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant) :
#61. Increasing air pressure will have the following effect on the drag of an aeroplane (angle of attack, OAT and TAS are constant):
#62. Which statement is correct? The lift to drag ratio provides directly the
#63. The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from :
#64. Which statement about induced drag and tip vortices is correct?
#65. Which of the following wing planforms gives the highest local profile lift coefficient at the wingroot ?
#66. If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually : (flap span less than wing span)
#67. The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with:
#68. Induced drag at constant IAS is affected by:
#69. Which of the following will reduce induced drag?
#70. Induced drag is created by the:
#71. What is the effect of high aspect ratio of an aeroplane’s wing on induced drag?
#72. Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)
#73. Induced drag may be reduced by:
#74. The induced drag:
#75. The relationship between induced drag and the aspect ratio is:
#76. A high aspect ratio wing produces:
#77. Excluding constants, the coefficient of induced drag (CDi) is the ratio of :
#78. High Aspect Ratio, as compared with low Aspect Ratio, has the effect of :
#79. Winglets
#80. Which location on the aeroplane has the largest effect on the induced drag ?
#81. The induced angle of attack is the result of:
#82. The induced drag coefficient, CDi is proportional with:
#83. The interference drag is created as a result of
#84. The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
#85. In what way do (1) induced drag and (2) parasite drag alter with increasing speed?
#86. An aeroplane accelerates from 80 kt to 160 kt at a load factor equal to 1. The induced drag coefficient (i) and the induced drag (ii) alter with the following factors:
#87. What is the effect on induced drag of weight and speed changes ?
#88. How does the total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight?
#89. Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?
#90. At an aeroplane’s minimum drag speed, what is the ratio between induced drag Di and profile drag Dp? Di/Dp=
#91. The aeroplane drag in straight and level flight is lowest when the:
#92. What will happen in ground effect ?What will happen in ground effect ?
#93. If an aeroplane flies in the ground effect
#94. Floating due to ground effect during an approach to land will occur :
#95. Ground effect has the following influence on the landing distance :
#96. An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:
#97. 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:
#98. Which of the following statements about boundary layers is correct?
#99. Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?
