In trophoshere temperature: Stays practically constant. By altitude increases. By altitude decreases.
The air particles in the laminar boundary layer: Move from on layer to another. Sometimes move from one layer to another. Do not move from one layer to another.
The turbulent boundary layer produces: The same friction drag than laminar boundary layer. Extremely more friction drag than laminar boundary layer. Less friction drag as the laminar boundary layer.
The angle btw the cord line of the profile and the longitudinal axis of the aircraft is known as: The angle of attack. The angle of deviation. The angle of incidence.
When the position of the center of lift (CP) moves forward of the position of the center of gravity (CG) we have: A nose up reaction. A level flight. A nose down reaction.
Lift augmentation devices: Increase the lift at high speed flight (cruise). Decrease the lift at low speed flight (take off and landing). Increase the lift at low speed flight (take off and landing).
With the flaps lowered, the stalling speed will: Increase. Decrease. Remain the same.
An aircraft with negative static stability has: Tends to return to original state after being disturbed. To remain in new position after being disturbed. Tends continuing movement away from original state after being disturbed.
The control surface which gives longitudinal control is: The rudder. The ailerons. The elevators.
Longitudinal stability is given by: The wing dihedral. The horizontal trimeable stabilizer. The ailerons.
The height of Tropopause is approximately 8km over: The North and Equator. The Equator and South pole. The North and South pole.
Generally CP travels along the chord line by AOA change. Higher AOA- CP moves forward. Otras.
A straight line drawn between the leading and trailing edge is called: Chord line Otras.
What is the definition of acceleration? (2.2) Acceleration is the change in velocity. Acceleration is the distance that a moving objets cover in a unit of time. Acceleration is the change in velocity divided by the time during which the change takes place.
Only laminar Flow over the wing Surface can produce lift (2.3) True. False, because turbulent flow also produces very small amount of lift. True, but only when flying below 100km/h.
Wing fences are used to reduce. (3.18) CD. CL The effects of the span-wise flow.
When the wing tip stall occurs. (3.14) (3.15) The center of lift is moved backward. The center of lift is stays unchanged. The center of lift is moved forward.
Stall conditions on swept wings first occur at: (3.15) (3.14) In the root of the wing. On the lower surface of the wing. Wing tip área.
When rudder is used to give a coordinated turn to the left (3.6) The left pedal is moved forward and the rudder moves right. The right pedal is moved forward and the rudder moves right. The left pedal is moved forward and the rudder moves left.
What are two main types of stability: (4.3) Static stability and lateral stability. Lateral stability and directional stability. Static stability and dynamic stability.
The control surface which gives longitudinal control is: (4.4) (4.3) The rudder. The ailerons. The elevators.
If the angle of attack (AOA) is increased above the stalling angle (2.13) Lift and drag both decreases. Lift will decrease and drag will increase. Lift and drag both increase.
Water vapors are: (1.4) Ligther than perfectly dry air. Heavier than perfectly dry air. Heavier than water.
How can we calculate coefficient of drag? (2.11) Measured drag divided by measured lift. It is the ratio of the drag pressure to Dynamic pressure. Measured drag multiplied by theoretical drag.
Most optimal AOA to produce most lift and least drag in: (2.12) Around 15o AOA. Around 6o AOA. (entre 4 y 8) Around 2o AOA.
Normal shock wave leads (3.11) (3.13) To a large decrease in static pressure behind the wave. To a small decrease in static pressure behind the wave. To total turbulence behind the shock wave.
By increasing altitude temperature decreases and speed of sound: (3.12) (3.11) Stays the same. Decreases. Increases.
The directional stability depends on (4.8) Aircraft vertical tail only. Sweepback of the wing and vertical tail. Dihedral angle only.
Induced drag is reduced by: (2.15) Higher aspect ratio. Higher angle of diedral. All of the above.
When air flows through the venturi tube decreased area: (2.3) Velocity increases and static pressure decreases. Velocity increases and dynamic pressure decreases. Velocity decreases and static pressure increases.
Critical Mach number is the boundary between: (3.11) Supersonic and Hypersonic speed. Transonic and supersonic speed. Subsonic and Transonic speed.
Which statement is true relative to changing angle of attack: (2.13) An increase in angle of attack will increase drag. Otros.
The resistance or skin friction of the air as it passes along the surface of a wing is a type of: (2.15) Induced drag. Form drag. Parasite drag.
Generally CP travels along the chord line by AOA change. (2.13) Lower AOA - CP moves forward. Higher AOA - CP moves forward. Power= Force/area.
A straight line drawn between the leading and trailing edge is called: (2.8) Mean camber line. Camber. Chord line.
The maximum coefficient of lift correspond to the: (2.15) Maximum angle of attack. Otros.
When a supersonic airflow passes through a shockwave we have sudden changes in: (3.13) Density, pressure, temperature, velocity. Otros.
The ratio of the True Air Speed (TAS) to sound speed is known as: (3.12) Mach number. Otros.
At zero angle of attack, the static pressure along the upper and lower surface of a symmetrical airfoil would be: (2.12) Equal to atmospheric pressure Otros.
Point of stagnation is the point where: (2.3) The velocity of the air is 0. Otros.
Dynamic stability refers to how the continuous motion of a body: (4.4) Varies over displacement. Otros.
Winglets or sharklets: (3.17) Reduce wave drag. Otros.
According to ICAO the temperature of International standard atmosphere at sea level is: (1.6) 15 grados. Otros.
Which profile has the lowest from drag? (2.14) Wing airfoil Otros.
Most civil fan engine driven aircraft files: (2.16) Between 0,75 and 0,85 mach. Otros.
The turbulence caused by wing tip vortices absorbs energy and (2.15) Increases the induced drag. Decreases the drag. Keeps the drag constant throughout the flight.
Atmosphere is the same as: (1.3) 14,7 pasi, 29,92 in Hg or 1013,2 hPa. 14,7 mbar , 29,92 in Hg or 1013,2 psi. 14,7 psi, 29,92 mm hg or 1013,2 hPa.
Density is: (1.4) Mass per unit of volume. Weight per unit of time. Mass per unit of time.
What happens with the temperature between tropopause and ozone layer? (1.5) The temperature increases. The temperature decreases to about -80 degrees C. The temperature remains constant.
Lift drag (L/D) ratio: (2.11) Presents airfoil CP. Indicates airfoil efficiency. The efficiency of the length of the wing.
What is form drag? (2.14) Type of parasite drag, which depends on friction of the air flowing over the wing surface. Type of parasite drag, which depends on shape - form of the object. Type of parasite drag, which depends on the length of the wings.
On a geometrically twisted wing the camber of the profile is contant across the span of the wing but the angle of incidence is: (2.8) Constant across the wing span. Greater at the root than at the tip. None of above.
Newton’s law of motion is: (2.2) His second law and it says F=ma. His first law and it says F=ma. His first law and it says F=m/a.
Aircraft constructors fix: (3.2) CG aft of the CP. CG forward of the CP. CG at the same point as CP.
Why do we use flaps for: (3.6) To increase lift and consequently we increase drag. To decrease lift and drag. To increase drag and decrease lift.
Lateral stability is the stability of the aircraft around: (4.7) The lateral axis The longitudinal axis. The vertical axis.
Lift produced by an airfoil is the resultant force developed perpendicular to: (2.12) The relative wind. The cord line. The longitudinal axis of the aircraft.
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