Theory Of Flight Flashcards
Downstream of a normal shockwave
Pressure and temperature increase
Immediately downstream of a normal shockwave, air is always
Subsonic
Immediately downstream of an oblique shock wave is always
Supersonic
Downstream of a normal shockwave
Pressure and temperature increase
At speeds above Mach 1, shockwaves will form above and below the wing,
At both the leading and trailing edge
At speeds greater than mach 1, airflow in the boundary layer is
Subsonic
Air either side of an oblique shockwave is generally,
Supersonic
A shock wave in a very thin region in which there is a sudden decrease of
Velocity
Correct order of configuration to give an increasing critical angle of attack:
Trailing edge flaps extended, clean wing, slats extended
Series of configurations increasing critical angle of attack:
Flaps only extended, clean wing, slats only extended
At speeds greater than Mach 1, airflow in the boundary layer is
Subsonic
What pitching moment will be generated when fowler flaps are deployed on an aircraft with a high mounted (T-tail) tail plane?
An aircraft nose down pitching moment
The higher speed of the high wing in a banked turn causes it to have more drag than the low wing, this may be compensated for by?
use of the rudder control
The outboard ailerons on some aircraft…
Are isolated to prevent aileron reversal
Feedback on a PFCU is?
Used on all PFCUs
When the centre of gravity moves to the same position as the centre of pressure, what happens to stability and controllability?
Stability decreases, controllability increases
A flying control mass balance weight
Tends to move the control surface C of G close to the hinge line
The increase in skin temperature, due to aerodynamic heating, of a high speed aircraft is approximately proportional to?
The square of the aircraft speed
A shock wave is a very thin region in which there is a sudden decrease of?
Velocity
When airflow velocity over an per cambered surface of an aerofoil decreases, what takes place?
Pressure increases, lift decreases
What is the effect on TAS if altitude is increases to 35,000 ft while flying at a constant Mach number?
Decrease
During a flap down selection in a continuous straight and level flight at constant IAS and weight
The centre of pressure moves aft
The angle of attack at which an aircraft stalls…..
Remains the same regardless of weight
If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (Flap span less than wing span)
Increase
