# Applied Aerodynamics Test 4

After answering this aerodynamic test, the next test is supersonic aerodynamics.

1. Yaw is defined as the movement of the longitudinal axis about which axis?
• A. Lateral
• B. Longitudinal
• C. Vertical
• D. Horizon
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. Minimum Thrust Required is achieved when
• A. Max Aerodynamic Efficiency
• B. Min Aerodynamic Efficiency
• C. Minimum Power Required
• D. Maximum Power Available
1. 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
1. 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%
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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
1. 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