Q1. If aerodynamic balancing is increased, what is the effect on the CP of the control surface?
A: It is not effected
B: It moves rearward
C: It moves forward
Q2. During deployment of flaps and slats, the lift vector?
A: Moves rearwards
B: Remains the same
C: Moves forwards
Q3. An advantage of locating engines at the rear of the fuselage, in comparison to a location under the wing is?
A: Less influence on longitudinal control on thrust changes
B: Lighter wing construction
C: A wing is less sensitive to flutter
Q4. How do vortex generators work?
A: Re direct slantwise airflow
B: Take energy from the free stream and introduce it into the boundary layer
C: Reduce the adverse pressure gradient
Q6. On a swept wing aeroplane at low speed, the pitch up phenomenon?
A: Is caused by wingtip stall
B: Is caused by extension of trailing edge lift augmentation devices
C: Never occurs, since a swept wing is a remedy to pitch up
Q7. A wing stalling angle is?
A: Unaffected by a turn
B: Decreased in a turn
C: Increased in a turn
Q8. What is the effect on TAS if altitude is increased to 35,000 ft while flying at a constant mach number?
A: Remain the same
C: Increase then remain constant
Q9. If Vs is 100 kt in straight and level flight, during a 45 degree bank turn, Vs will be?
A: 140 Kts
B: 119 Kts
C: 100 Kts
Q10. When the trailing edge flap is extended?
A: The CP moves forward but the C of G remains the same
B: The CP moves forward and the pitching moment changes to nose up
C: CP moves rearwards
The aeroplane fin is of symmetrical aerofoil section and therefore will provide a side?
A: If a suitable AOA develops due to either yaw or rudder movement
B: Only if a suitable AOA develops due to yaw
C: Only when rudder is moved