Free Printable CPD222 Final 2/65

1.

The effect that increased mass has on a glide descent is:

a)

(a) it increases the vertical speed

b)

(b) it increases the vertical and the horizontal speeds

c)

(c) it increases the distance travelled

d)

(d) it decreases the distance travelled

2.

Which of the following combinations of characteristics will affect the glide angle?

a)

(a) configuration and angle of attack

b)

(b) mass and altitude

c)

(c) altitude and configuration

d)

(d) configuration and mass

3.

Which of the following will increase the glide distance?

a)

(a) increased aeroplane mass

b)

(b) decreased aeroplane mass

c)

(c) a headwind

d)

(d) a tailwind

4.

In a glide descent, to fly for the maximum endurance the speed should be that for:

a)

(a) maximum lift

b)

(b) minimum drag

c)

(c) critical Mach number

d)

(d) the minimum angle of descent

5.

The lift coefficient decreases during a glide descent at a constant Mach number because the:

a)

(a) TAS decreases

b)

(b) glide angle decreases

c)

(c) IAS increases

d)

(d) aircraft mass decreases

6.

The effect a headwind will have on a climb to a specified altitude, compared with still air, is to:

a)

(a) increase the climb time

b)

(b) decrease the climb time

c)

(c) decrease the ground distance travelled

d)

(d) decrease the fuel used

7.

Increased mass will cause the climb performance to:

a)

(a) improve

b)

(b) be unchanged

c)

(c) be unchanged if the short-field technique is used

d)

(d) degrade

8.

A higher ambient temperature:

a)

(a) increases the angle of climb but decreases the rate of climb

b)

(b) does not affect climb performance

c)

(c) decreases the angle of climb and the rate of climb

d)

(d) decreases the angle of climb but increases the rate of climb

9.

A constant headwind component:

a)

(a) increases the angle of the climb path

b)

(b) increases the maximum rate of climb

c)

(c) decreases the angle of the climb path

d)

(d) increases the maximum endurance

10.

The effect that increased mass has on the gliding range is that it:

a)

(a) increases range

b)

(b) decreases range

c)

(c) has no effect on range

11.

High-speed buffet is induced by:

a)

(a) boundary-layer separation due to shockwaves

b)

(b) boundary-layer control

c)

(c) expansion waves on the upper surface of the wing

d)

(d) movement of the CG

12.

At the same Mach number, the normal shockwave compared with the oblique shockwave has a:

a)

(a) greater expansion

b)

(b) smaller compression

c)

(c) smaller expansion

d)

(d) greater compression

13.

The function of the Mach trimming device is to minimize the adverse effects of:

a)

(a) compressibility on the stabiliser

b)

(b) movement of the CP when at high speed

c)

(c) increased drag due to shockwave formation

d)

(d) uncontrolled changes in the stabiliser setting

14.

The increase of drag above the critical Mach number is due to:

a)

(a) wave drag

b)

(b) increased angle of attack

c)

(c) increased interference drag

d)

(d) increased skin friction

15.

After air has passed through a normal shockwave. Which of the following statements is correct?

a)

(a) The temperature increases.

b)

(b) The total pressure decreases.

c)

(c) The temperature decreases.

d)

(d) The velocity increases.

16.

Which of the following flight phenomena can happen at Mach numbers below Mcrit?

a)

(a) Mach buffet

b)

(b) shock stall

c)

(c) Dutch roll

d)

(d) tuck under

17.

The speed at which ‘tuck under’ will occur is:

a)

(a) only at the critical Mach number

b)

(b) only below the critical Mach number

c)

(c) above or below the critical Mach number depending on the angle of attack

d)

(d) only above the critical Mach number

18.

Compared with an oblique shockwave at the same Mach number, a normal shockwave has a:

a)

(a) lower static temperature

b)

(b) greater loss in total pressure

c)

(c) greater total pressure

d)

(d) greater total temperature

19.

If the Mach trimmer fails:

a)

(a) the aeroplane mass must be reduced

b)

(b) the maximum Mach number is limited

c)

(c) the CG must be moved aft

d)

(d) the speed must remain constant

20.

When comparing the characteristics of a straight wing with those of a swept wing that have the same wing area and loading, the swept wing has the advantage of:

a)

(a) increased longitudinal stability

b)

(b) lower stalling speed

c)

(c) higher critical Mach number

d)

(d) greater strength

21.

When air is passing through a shockwave the density will:

a)

(a) decrease

b)

(b) remain constant

c)

(c) decrease and then increase

d)

(d) increase

22.

At what speed does the front of a shockwave move over the earth’s surface?

a)

(a) the speed of sound at ground level

b)

(b) the speed of sound at cruising level

c)

(c) the TAS of the aeroplane

d)

(d) the groundspeed of the aeroplane

23.

How does decreased aeroplane mass affect Mcrit at a constant IAS?

a)

(a) Mcrit decreases as a result of flying at a higher angle of attack

b)

(b) Mcrit increases as a result of flying at a lower angle of attack

c)

(c) Mcrit increases as a result of compressibility effects

d)

(d) Mcrit decreases

24.

In straight and level flight when the Mach number is slowly increased the first shockwave will

occur:

a)

(a) on the underside of the wing

b)

(b) somewhere on the fin

c)

(c) somewhere on the horizontal tail

d)

(d) on the upper surface at the wing root

25.

The pressure distribution on the upper surface of the wing when all of the airflow is supersonic during acceleration changes to:

a)

(a) rectangular

b)

(b) triangular

c)

(c) irregular

d)

(d) laminar

26.

The large increase of drag experienced at high transonic speeds is due to the formation of the shockwave causing:

a)

(a) wave drag

b)

(b) increased parasite drag

c)

(c) increased induced drag

d)

(d) decreased thrust available

27.

A normal shockwave causes the airflow to:

a)

(a) increase speed from subsonic to supersonic

b)

(b) decrease speed from supersonic to subsonic

c)

(c) change direction

d)

(d) become laminar

28.

The reason that aeroplanes have a waisted fuselage is:

a)

(a) to increase the strength of the wing root

b)

(b) to improve stability at low speeds

c)

(c) to incorporate the engine nacelles

d)

(d) to comply with the area rule

29.

Increased drag in the transonic speed range is due to the:

a)

(a) skin friction

b)

(b) shockwave

c)

(c) angle of attack

d)

(d) parasite drag

30.

Shock-induced separation results in:

a)

(a) decreasing lift

b)

(b) constant lift

c)

(c) increasing lift

d)

(d) decreasing drag

31.

How does the thrust of a fixed-pitch propeller vary during take-off run? The thrust

a)

(a) increases slightly while the aeroplane builds up speed

b)

(b) only varies with mass changes

c)

(c) is constant during the take-off and climb

d)

(d) decreases slightly while the aeroplane builds up speed

32.

The angle of attack for a propeller blade is the angle between the chordline and:

a)

(a) the local airspeed vector

b)

(b) the direction of the propeller axis

c)

(c) the aeroplane heading

d)

(d) the principal direction of the propeller blade

33.

For a fixed-pitch propeller designed for the cruise, the angle of attack of each blade, measured at the reference section is:

a)

(a) lower in the ground run than in flight with the same RPM

b)

(b) always positive during an idle descent

c)

(c) is optimum when the aeroplane is in a stabilised cruise

d)

(d) decreased when the aeroplane speed is decreased at the same RPM

34.

The gyroscopic effect of the propeller is affected by:

a)

(a) roll and pitch

b)

(b) decreased blade angle

c)

(c) increased RPM

d)

(d) increased blade angle

35.

The effect of feathering a propeller is to:

a)

(a) minimize the lift/drag ratio

b)

(b) maximize the windmilling speed

c)

(c) improve the thrust produced

d)

(d) reduce the drag on the propeller to minimum

36.

A propeller blade is twisted from root to tip because:

a)

(a) maximum thrust is required from the tip

b)

(b) maximum thrust is required from the root

c)

(c) the local angle of attack is dependent on the TAS

d)

(d) the local angle of attack is dependent on the angular velocity

37.

The angle of attack of a fixed-pitch propeller for a general-purpose aeroplane:

a)

(a) is optimum during take-off

b)

(b) decreases with decreased speed at constant RPM

c)

(c) is optimum in stabilised cruising flight

d)

(d) is less during the take-off ground run than in level flight

38.

The torque of a clockwise turning propeller (when viewed from behind) produces a:

a)

(a) nose-up pitching moment

b)

(b) rolling moment to the left

c)

(c) nose-down pitching moment

d)

(d) rolling moment to the right

39.

The wing shape least affected by turbulence is:

a)

(a) straight wing

b)

(b) swept-back wing

c)

(c) swept-forward wing

d)

(d) elliptical wing

40.

Comparing the reaction of a multiengined turbojet aeroplane to that of a multiengined counterrotating turboprop aeroplane to an engine failure:

a)

(a) the turbojet aeroplane has the greater tendency to roll

b)

(b) both have the same tendency to roll

c)

(c) both have the same yawing tendency

d)

(d) the turboprop aeroplane has the greater tendency to roll

CPD222 Final 2/65

Total questions: 40

Worksheet time: 52mins

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