Revision Questions Aerodynamics Flashcards
When climbing at a content Mach number TAS will -
A. Decrease if temp decreases B. Decrease C. Decrease if temp increases D. Increase E. Remain constant
A. Decrease if temp decreases
The difference between leading edge slats and leading edge flaps is -
A. They are two names for the same device
B. Slats reenergise the boundary layer and flaps alter the effective camber of the leading edge
C. Flaps reenergise the boundary layer and slats alter the effective camber of the leading edge
D. Flaps decrease the stall speed while slats increase the stall speed
B. Slats reenergise the boundary layer and flaps alter the effective camber of the leading edge
Mcrit is -
A. That speed where all of the local airflow is supersonic
B. That speed where all of the local airflow is subsonic
C. That speed above which supersonic local airflow first occurs
D. None of the above
C. That speed above which supersonic local airflow first occurs
An aircraft exceeds Mcrit. Assuming no ‘Mach trimmer’ is fitted, the first thing to occur would be -
A. Nose pitch up
B. Severe vibration, buffet and structural failure
C. Compressor stall
D. Nose pitch down
D. Nose pitch down
Exceeding Mcrit results in a pitch nose down. This is because -
A. The CP moves rearward
B. The CP moves forward
C. The tail plane is producing excessive drag
D. None of the above
A. The CP moves rearward
A mach trimmer -
A. Trims the aircraft for the nominated mach number
B. Stops aircraft exceeding Mcrit
C. Ensures that with increasing speed the aircraft will tend to pitch down
D. Ensures that with increasing speed the aircraft will tend to pitch up
D. Ensures that with increasing speed the aircraft will tend to pitch up
On swept wing aircraft, nose pitch up at the stall is caused by -
A. Suddenly slat retraction
B. Elevator stall combined with a rearward C of G movement
C. Wingtip stall and the effective CP moving rearwards
D. Wingtip stall and the effective CP moving forwards
D. Wingtip stall and the effective CP moving forwards
Vs when related to transport category aircraft is -
A. The minimum steady flight speed
B. The speed at which the aircraft stalls
C. Excess power over weight
D. Excess thrust over drag
A. The minimum steady flight speed
You have descended to hold at 3000ft. At this altitude your ideal holding speed would primarily be determined by -
A. Engine RPM considerations
B. IAS considerations
C. Flap extension limits
D. Body angle limits
B. IAS considerations
Swept wing aircraft employ a stick pusher system. The operates at -
A. 1.3Vs
B. 10kt above the stalling speed
C. The speed below which controlled level flight is not sustainable
D. 15 degrees angle of attack
C. The speed below which controlled level flight is not sustainable
Jet aircraft over speed warnings will operate -
A. At Vmo/Mmo
B. Slightly above Vmo/Mmo
C. Slightly below Vmo/Mmo
D. Slightly below Vdf/Mdf
B. Slightly above Vmo/Mmo
Mdet is -
A. Mcrit plus an allowance which varies for each aircraft type
B. That aircraft speed where the first local sonic flow occurs
C. That aircraft speed above which all the local flow is supersonic
D. The maximum Mach number for a particular aircraft type
C. That aircraft speed above which all the local flow is supersonic
Optimum range is achieved for flying at -
A. A constant flight level, 1.32 Vimd and max cruise RPM
B. A cruise climb, 1.32 Vimd and max continuous RPM
C. A constant flight level, 1.32 Vimd and design RPM
D. A cruise climb, 1.32 Vimd and design RPM
D. A cruise climb, 1.32 Vimd and design RPM
Climb IAS decreases with increased altitude because -
A. Maximum excess power occurs at a lower IAS at high altitude
B. Maximum excess power occurs at a lower TAS at high altitude
C. A constant angle of attack is required
D. The engines are producing less thrust as altitude increases
A. Maximum excess power occurs at a lower IAS at high altitude
For a given altitude and weight, the IAS variation for max angle of climb if flap is extended is -
A. It increases to take advantage of the extras lift
B. It remains the same as the weight is the same
C. It decreases to maintain a lower minimum drag speed
D. It increases to maintain a higher minimum drag speed
C. It decreases to maintain a lower minimum drag speed
Concerning slotted flaps and/or fowler flaps -
A. Slotted flaps increase the chord and preserve the energy in the boundary layer of the airflow while fowler flaps increase the camber and chord
B. Slotted flaps increase the camber and preserve the energy in the boundary layer of the airflow while Fowler flaps increase the camber and chord
C. Fowler flaps increase the chord and preserve the energy in the boundary layer of the airflow while slotted flaps increase the camber and chord
D. Fowler flaps increase the camber and preserve the energy in the boundary layer of the airflow while slotted flaps increase the camber and chord
B. Slotted flaps increase the camber and preserve the energy in the boundary layer of the airflow while Fowler flaps increase the camber and chord
A nose down pitch change in an aircraft flying near Mcrit would be most likely to be caused by -
A. The Mach trimmer
B. A rearwards CP shift
C. A forwards CP shit
D. Jack stalling
B. A rearwards CP shift
The minimum control speed ground (Vmcg) is lower than minimum control speed air (Vmca) because -
A. Pedal nose wheel steering is available on the ground
B. Differential braking is available on the ground
C. The main wheels are on the ground
D. Tiller nose wheel steering is available on the ground
C. The main wheels are on the ground
Any head or tail wind component will reduce the distance to a PNR
True or False
True
The angle of attack required for maximum range cruise does not vary with aircraft gross weight
True or false
True
For a single sector with constant TAS, an increased wind component will always decrease the distance from departure to the PNR
True or false?
True
Vmca of a twin engine turbo prop aircraft is determined on control with the critical engine inoperative and with a centre of gravity at the -
A. Most forward position
B. Most rearward position
C. CP position
D. Mid range position
B. Most rearward position
Rear CP = less rudder authority
Forward CP better for stall
In a supersonic airstream, the static pressure behind the expansion wave -
A. Decreases
B. Increases
C. Remains constant
D. Increases then decreases
A. Decreases
Velocity increasing in a expansion wave
The environmental variable which will result in an increased Vmca in a multi engine aeroplane is an increase in -
A. Temperature
B. Density
C. Pressure altitude
D. Humidity
B. Density
Vmca is based on power output / engine performance of live engine
A B767 is in cruise with the stabiliser trim set correctly for a relatively forward centre of gravity. The position of the elevator would be -
A. Up
B. Down
C. Faired
D. Automatically adjusted by the autopilot
C. Faired
ELEVATOR position
An increase in gross weight will cause the position of the total drag curve to move -
A. Up and left
B. Up and right
C. Down and left
D. Down and right
B. Up and right
The deployment of spoilers, gear or flap will cause the position of the total drag curve to move -
A. Up and left
B. Up and right
C. Down and left
D. Down and right
A. Up and left
In a steady asymmetric flight in a twin engined jet transport category aircraft, the crew elect to level the wings with rudder input. The position of the balance ball in this situation will be -
A. Half a ball toward failed engine
B. Half a ball toward live engine
C. Fully deflected toward operating engine
D. Centred
D. Centred
You’re at an unusually high flight level for the current gross weight of the aircraft and cruising at normal cruise speed. During a manoeuvre you feel airframe buffet
The likely cause is -
A. High speed buffet because of the altitude
B. Low speed buffet because of the altitude
C. Either low speed or high speed buffet
D. Clear air turbulence
C. Either low speed or high speed buffet
‘Coffin corner’
The yaw damper of a jet transport aircraft receives its yaw information control from -
A. The attitude gyro
B. The directional gyro
C. The rate gyro
D. The azimuth gyro
C. The rate gyro
The transition in airflow speed marked by a normal shockwave and any accompanying change in airflow direction is -
A. From supersonic to subsonic, with no change in direction
B. From subsonic to supersonic, with change in direction
C. From subsonic to supersonic, with no change in direction
D. From supersonic to subsonic, with a change in direction
A. From supersonic to subsonic, with no change in direction
A jet transport aircraft demonstrates positive oscillatory stability at 1000ft but instability at 9000ft
The change in aerodynamic damping and associated speed change which causes this is -
A. Reduced aerodynamic damping due to increased TAS
B. Increased aerodynamic damping due to increased TAS
C. Reduced aerodynamic damping due to increased EAS
D. Increased aerodynamic damping due to increased EAS
A. Reduced aerodynamic damping due to increased TAS
When a swept wing aircraft suffers a wingtip stall, the centre of pressure moves -
A. Inwards and forward
B. Outwards and aft
C. Inwards and backwards
D. Outwards and forwards
A. Inwards and forward
With an increase in altitude, the longitudinal stability of an aircraft -
A. Increases
B. Decreases
C. Remains constant
D. Increases to the tropopause then decreases
B. Decreases
Buffet boundaries for a jet transport category aircraft will increase with an increase in -
A. Altitude
B. Gross weight
C. Mach number
D. Fuel burn
D. Fuel burn
Buffet boundaries increase with a lower weight
