POF revisits Flashcards
Assume that after t/o a turn is made to a downwind hdg. In regard to the grd, the aeroplane will climb at
STEEPER ANGLE into the wind than downwind
When AOA of symmetrical aerofoil is inc, the CP ( centre of px) will ___
Remain unaffected
An aircraft has a L/D ratio is 15:1 at 50 kts in calm air. What would be the L/D ratio with a direct headwind of 25kts
15:1
Inc or Dec in wt has no effect in L/D ratio
The best L/D ratio of an a/c in a given configuration is a value that ____
Remains constant regardless of IAS changes
Wing w a higher aspect ratio will have ____ than a lower aspect ratio
Lower stall speed
What happens to tot drag when accelerating from CLmax to max speed
Total drag Dec then inc
If the aircraft weight is increased without change of C of G position, the stalling angle of attack will
Remain the same
For an aircraft if steady turn stall speed and angle of attack would be
Higher stall speed but same AOA
Sweep back on wing will inc tendency of ___
Tip stalling
Highly tapered wing without wing twist the stall will commence at ___
At the tip
Purpose of bdry layer fence on a swept back wing is to ___
To control spanwise flow and delay tip stall
Slots inc the stalling angle of attack by
Delaying separation
On an untapered wing without twist the downwash inc from ____
Inc from root to tip
Vortex generators are used to
Reduce boundary layer sep
Wing mounted stall warning detector came would be situated ____
At LE
On lower sfc
Input date to a stalk warning device system is
Angle of attack
And is some systems rate of change of angle of attack
In a developed spin the angle of attack of wings ___
angle of attack of both the wings will be positive
Indications of icing induced stall can be
Violent roll oscillations
Airframe buffet
Violent wing drop
Extremely high rate of descents while in a normal flt attitude
If a single engine prop a/c is stalled power on in a climb turn to left
What should be the recovery action
Elevator stick fwd
Ailerons stick neutral
Rudder to prevent wing drop
Purpose of centrifugal latch on a single acting prop ____
Is to prevent feathering (fully course pitch from fully fine pitch) on shut down
(Overnight)
If the wing AC is forward of the CG
changes in lift produce a wing pitching moment which acts to increase the change of lift
If a disturbing force causes the aircraft to roll
wing dihedral will cause a rolling moment which reduces the sideslip
Dihedral gives a stabilising rolling moment by causing an increase in lift
on the lower wing if the aircraft is sideslipping
Sweepback of the wings will:
increases lateral stability at all speeds
Dihedral angle is
the upward and outward inclination of the main places to the horizontal datum
Aileron reversal would be most likely to occur:
flexible wing and
high airspeeds
if ailerons are def to 10deg instead of 5 deg it will cause
inc in rate of roll
What should be the feel on a ‘full and free’ check of the controls
a solid stop
If an aileron is moved downward
the stalling angle of that wing
the stalling angle of that wing is DECREASED
An aircraft takes off with the elevator control locks still in position. It is found to be nose heavy:
backward movement of the trim wheel would increase nose heaviness
To achieve the same degree of longitudinal trim, the trim drag from a variable incidence trimming tailplane would be:
less than that from an elevator
variable incidence trimming tailpane is better than nnormal trim tabs
The structure will continue to distort until it breaks
What is it called ?
Divergence
What is a Flutter
The rapid and uncontrolled oscillation of a surface resulting from imbalance.
Flutter normally leads to a catastrophic failure of the structure
Backlash
Possibility of movement of control sfc without any pilot’s input
What is the purpose of fitting the engine to an aircraft using wing mounted pylons
The wing structure can be lighter because the engine acts as a mass balance and also relieves wing bending stress
Aileron reversals at high dy pressures is caused by __
Dynamic pressure acting on aileron ,twisting the wing in the opposite direction, possibly causing the aircraft to bank in a direction opposite to that intended
