Theory Of Flight

Question 1

Downstream of a normal shockwave

Answer 1

Pressure and temperature increase

Question 2

Immediately downstream of a normal shockwave, air is always

Answer 2

Subsonic

Question 3

Immediately downstream of an oblique shock wave is always

Answer 3

Supersonic

Question 4

Downstream of a normal shockwave

Answer 4

Pressure and temperature increase

Question 5

At speeds above Mach 1, shockwaves will form above and below the wing,

Answer 5

At both the leading and trailing edge

Question 6

At speeds greater than mach 1, airflow in the boundary layer is

Answer 6

Subsonic

Question 7

Air either side of an oblique shockwave is generally,

Answer 7

Supersonic

Question 8

A shock wave in a very thin region in which there is a sudden decrease of

Answer 8

Velocity

Question 9

Correct order of configuration to give an increasing critical angle of attack:

Answer 9

Trailing edge flaps extended, clean wing, slats extended

Question 10

Series of configurations increasing critical angle of attack:

Answer 10

Flaps only extended, clean wing, slats only extended

Question 11

At speeds greater than Mach 1, airflow in the boundary layer is

Answer 11

Subsonic

Question 12

What pitching moment will be generated when fowler flaps are deployed on an aircraft with a high mounted (T-tail) tail plane?

Answer 12

An aircraft nose down pitching moment

Question 13

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?

Answer 13

use of the rudder control

Question 14

The outboard ailerons on some aircraft…

Answer 14

Are isolated to prevent aileron reversal

Question 15

Feedback on a PFCU is?

Answer 15

Used on all PFCUs

Question 16

When the centre of gravity moves to the same position as the centre of pressure, what happens to stability and controllability?

Answer 16

Stability decreases, controllability increases

Question 17

A flying control mass balance weight

Answer 17

Tends to move the control surface C of G close to the hinge line

Question 18

The increase in skin temperature, due to aerodynamic heating, of a high speed aircraft is approximately proportional to?

Answer 18

The square of the aircraft speed

Question 19

A shock wave is a very thin region in which there is a sudden decrease of?

Answer 19

Velocity

Question 20

When airflow velocity over an per cambered surface of an aerofoil decreases, what takes place?

Answer 20

Pressure increases, lift decreases

Question 21

What is the effect on TAS if altitude is increases to 35,000 ft while flying at a constant Mach number?

Answer 21

Decrease

Question 22

During a flap down selection in a continuous straight and level flight at constant IAS and weight

Answer 22

The centre of pressure moves aft

Question 23

The angle of attack at which an aircraft stalls…..

Answer 23

Remains the same regardless of weight

Question 24

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)

Answer 24

Increase

Question 25

If the weight of an aircraft is increased, the maximum lift to drag ratio will?

Answer 25

Not be affected