After answering this aerodynamic test, the next test is supersonic aerodynamics.
- Yaw is defined as the movement of the longitudinal axis about which axis?
- A. Lateral
- B. Longitudinal
- C. Vertical
- D. Horizon
- Aerodynamic forces and moments exerted on a body moving through a fluid stem from two sources:
- A. Pressure distribution and Shear stress distribution
- B. Lift and Drag Distribution
- C. Thrust and weight Distribution
- D. Thermal and Age distribution
- The net aerodynamic forces can be resolved into what two component forces?
- A. Lift and drag
- B. Weight and drag
- C. Thrust and drag
- D. Dynamic and static pressure
- What must you do to remain in formation as your aircraft takes on fuel (increasing weight) from the tanker that is maintaining a constant altitude and true airspeed?
- A. Maintain a constant AOA and TAS
- B. Decrease AOA and increase TAS
- C. Increase AOA and maintain constant TAS
- D. Increase AOA and TAS
- High density altitude will:
- A. Decrease the power produced by an engine and increase the thrust produced by the propeller or jet
- B. Increase the power produced by an engine and increase the thrust produced by the propeller or jet
- C. Decrease the power produced by an engine and decrease the thrust produced by a propeller or jet
- D. Increase the power produced by an engine and decrease the thrust produced by the propeller or jet
- All motion or changes in aircraft attitude occurs about which position?
- A. Aerodynamic center
- B. Center of pressure
- C. Center of gravity
- D. The cockpit
- For a given altitude, what are the properties of the input provided by the static pressure port in the pitot-static system?
- A. The static pressure value will vary with changes in aircraft true airspeed (TAS)
- B. The static pressure value will vary with changes in aircraft angle of attack (AOA)
- C. The static pressure value will vary with changes in aircraft weight
- D. The static pressure value will vary with changes in atmospheric ambient static pressure and altitude
- Two planes leave manila for southern city, a distance of 900 km. plane A travels at a ground speed of 90 kph faster than the plane B.
Plane A arrives in their destination 2 hours and 15 minutes ahead of plane B. what is the ground speed of plane A?
- A. 205 KPH
- B. 315 KPH
- C. 240 KPH
- D. 287 KPH
- When the value on the aircraft indicated airspeed (IAS) indicator equals the aircraft true airspeed (TAS)
- A. When static pressure at aircraft altitude is less than static pressure at sea level, on a standard day
- B. When static pressure at aircraft altitude is greater than static pressure at aircraft sea level, on a standard day
- C. When static pressure at aircraft altitude equals static pressure at sea level, on a standard day
- D. When static pressure at aircraft altitude equals density at sea level, on standard sea level
- An aircraft is climbing at a constant 350 KIAS. What change occurs in Mach number as altitude increases?
- A. Mach number increases
- B. Mach number decreases
- C. Mach number remains constant
- D. There is no Mach number at this speed
- Due to friction along the connections of engine components such as gears, lobes, shafts and any mechanical transmission would tend to
- A. Reduce the power being transmitted
- B. Increase the power being transmitted
- C. Multiply the power being transmitted
- D. Nothing happens to the power being transmitted
- Minimum Thrust Required is achieved when
- A. Max Aerodynamic Efficiency
- B. Min Aerodynamic Efficiency
- C. Minimum Power Required
- D. Maximum Power Available
- The altitude at which the max R/C = 100 ft/min is the
- A. Service ceiling
- B. Landing run
- C. Take-off run
- D. Absolute ceiling
- In order to ensure a margin of safety during take-off, the lift-off velocity is typically _ higher than the stalling velocity
- A. 20%
- B. 25%
- C. 30%
- D. 35%
- For the maneuvering performance of airplanes, it is advantageous to have the smallest r and the smallest ω obtainable by
- A. Have the highest Load factor and The lowest possible velocity
- B. Have the lowest Load factor and The highest possible velocity
- C. Have the highest Load factor and The highest possible velocity
- D. Have the lowest Load factor and The lowest possible velocity
- The force acting perpendicular to the relative wind and in the same direction as the flight path is known as:
- A. Thrust
- B. Lift
- C. Weight
- D. Drag
- The force acting parallel with the relative wind and in the opposite direction to the flight path is known as:
- A. Thrust
- B. Lift
- C. D. Drag
- Weight
- The force acting parallel with the relative wind and in the same direction as the flight path is known as:
- A. Thrust
- B. C. Weight
- D. Drag
- The force acting perpendicular to the relative wind and in the opposite direction to the flight path is known as:
- A. Lift
- B. Weight
- C. Drag
- D. Force acting parallel with the relative wind and in the opposite direction
- If the same angle of attack is maintained in ground effect as when out of ground effect, lift will:
- A. Increase, and induced drag will increase
- B. Increase, and induced drag will decrease
- C. Decrease, and induced drag will increase
- D. Decrease, and induced drag will decrease
- On a wing, the force of lift acts perpendicular to, and the force of drag acts parallel to the:
- A. Camber line
- B. Longitudinal axis
- C. Chord line
- D. Flight path
- An airfoil section is designed to produce lift resulting from a difference in the:
- A. Negative air pressure below and a vacuum above the surface
- B. Vacuum below the surface and greater air pressure above the surface
- C. Higher air pressure below the surface and lower air pressure above the surface
- D. Higher air pressure at the leading edge than at the trailing edge
- When the angle of attack of a symmetrical airfoil is increased, the center of pressure will: A. Have very limited movement
- B. Move aft along the airfoil surface
- C. Remain unaffected
- D. Move forward to the leading edge
- Why does increasing speed also increase lift?
- A. The increased impact of the relative wind on an airfoil’s lower surface creates a greater amount of air being deflected downward
- B. The increased speed of the air passing over an airfoil’s upper surface decreases the static pressure, thus creating a greater pressure differential between the upper and lower surfaces
- C. The increased velocity of the relative wind overcomes the increased drag
- D. Increasing speed decreases drag
- The point on an airfoil section through which lift acts is the:
- A. midpoint of the chord
- B. center of gravity
- C. center of pressure
- D. Aerodynamic center
- A line drawn from the leading edge to the trailing edge of an airfoil section and equidistant at all points from the upper and lower contours is called the:
- A. Chord line
- B. Camber
- C. Mean camber line
- D. Longitudinal axis
- When considering an airfoil section at a constant angle of attack, which of the following statements is true:
- A. If the static pressure on one side is reduced more than on the other side, a pressure differential will exist.
- B. If dynamic pressure is increased, the pressure differential will decrease
- C. The pressure differential will increase if the dynamic pressure is decreased
- D. Dynamic pressure and pressure differential are not related
- At zero angle of attack, the pressure along the upper surface of a symmetrical airfoil section would be:
- A. Greater than atmospheric pressure
- B. Equal to atmospheric pressure
- C. Less than atmospheric pressure
- D. Non-existent
- What is the effect on total drag of an aircraft if the airspeed decreases in level flight below that speed for maximum L/D?
- A. Drag increases because of increased induced drag
- B. Drag decreased because of lower induced drag
- C. Drag decreases because of increased parasite drag
- D. Drag decreases because of lower parasite drag
- By changing the angle of attack of a wing, the pilot can control the airplane’s:
- A. Lift and airspeed, but not drag
- B. Lift, gross weight, and drag
- C. Lift, airspeed, and drag
- D. Lift and drag, but not airspeed