If the velocity in a stream tube is increased, the streamlines:

(d) are not affected by the velocity

The angle of attack of an aerofoil is the angle between the:

(b) chordline and the undisturbed airflow

(a) longitudinal axis and the chordline

(c) longitudinal axis and the horizontal

(d) longitudinal axis and the undisturbed airflow

Lateral wing dihedral is the angle between the 0.25 chordline and the:

(c) longitudinal horizontal axis

Angle of attack of a wing is defined as:

(c) the angle between the wing chordline and the direction of the relative airflow

(a) the angle between the aeroplane longitudinal axis and the wing chordline

(b) the angle to obtain the maximum lift/drag ratio

(d) the angle between the climb path and the horizontal

In a constant TAS climb the Mach number will:

(c) decrease to FL100 and then increase

Assuming ISA conditions, and all other conditions are constant then if an aeroplane flies at the same angle of attack in straight and level flight at two different altitudes then the TAS will be:

(b) higher at the higher altitude.

(a) lower at the higher altitude.

(c) the same at both altitudes.

For two aeroplanes flying in a standard atmosphere at the same mass and the same IAS at different altitudes the relationship of their TAS is:

(b) greater at the higher altitude

(a) greater at the lower altitude

(d) less at the higher altitude

If the total sum of the moments about one axis of an aeroplane is not zero it would:

(d) have an angular acceleration about that axis

Two similar aeroplanes with wing-mounted engines one jet and the other propeller driven, in the event of an engine failure:

(a) the propeller aeroplane has the greater roll tendency

(b) they will both have the same yaw tendency

(c) they will both have the same roll tendency

(d) the propeller aeroplane will have the least roll tendency

If the stabiliser is jammed in the flight cruise position what action should be taken for landing?

(d) Select a higher landing speed and/or use a lower flap setting.

(a) Select a lower landing speed.

(b) Relocate as many passengers as possible forward.

One of the advantages of siting the engines on the rear fuselage compared with beneath the wings is:

(b) changes of thrust have less influence on the longitudinal control

(d) the wing is less sensitive to flutter

To maintain a constant pitching moment with an increase of thrust, for an aeroplane with engines mounted below the wing, the elevator deflection is:

(c) is dependent on the CG location

The lift and drag forces of a wing cross-section:

(a) depend on the pressure distribution around the wing for their magnitude

(b) are normal to each other at only one angle of attack

(c) are proportional to each other at all angles of attack

(d) vary linearly with the angle of attack

Which of the following statements regarding induced drag and wing-tip vortices is correct?

(c) The flow direction on the upper surface has a component towards the wing root and on the lower surface the flow direction has a component towards the wing tip.

(a) The direction of flow on the upper and lower surfaces deviates in the wing tip direction.

(b) The wing-tip vortices and the induced drag decrease with increasing angles of attack.

(d) Vortex generators diminish wing-tip vortices.

Winglets improve the performance of an aeroplane because they:

(b) decrease the static directional stability

(c) increase the manoeuvrability

(d) create an elliptical lift distribution

The greatest flow velocity over a cambered wing at a positive angle of attack is:

(d) in front of the stagnation point

The aerodynamic centre of a wing is the point, where:

(a) the pitching moment remains constant irrespective of the angle of attack

(b) the change of lift due to the variation of the angle of attack is constant

(c) aerodynamic forces are constant at the CP

(d) the aeroplane’s lateral axis intersects with the CG

Where streamlines converge in a two-dimensional flow pattern the static pressure will:

(b) increase initially and then decrease

When the angle of attack increases on an asymmetrical, single curve aerofoil in a subsonic airflow the CP will:

(d) remain at the aerodynamic centre

Wing-tip vortices are caused by:

(b) air spilling from the lower surface to the upper surface at the wing tip

(a) air spilling from the upper surface to the lower surface at the wing tip

(c) air spilling from the lower surface to the upper surface on the port and vice versa on the starboard

(d) the spanwise flow vector from the wing tip to the root on the lower surface

The advantage of a turbulent boundary layer over a laminar flow boundary layer is that:

(d) there is less tendency for it to separate

(c) it has greater skin friction

The lift force acting on an aerofoil:

(c) is mainly caused by suction on the upperside of the aerofoil

(a) is mainly caused by increased pressure beneath the aerofoil

(b) is the maximum at an angle of attack of 4◦

(d) is inversely proportional to the angle of attack up to 40◦

The point at which the aerodynamic lift acts on a wing is:

(d) the point of maximum wing chord

The factor that contributes most to the generation of lift is:

(a) increased pressure below the wing

(b) increased airflow velocity below the wing

(d) decreased airflow velocity above the wing

(b) parallel to the gravitational force

(a) perpendicular to the longitudinal axis

(c) perpendicular to the chordline

(d) perpendicular to the relative airflow

CPD240 Mid S/64 Quiz

40 questions

Show all answers

1.

MULTIPLE CHOICE QUESTION

1 min • 1 pt

The total pressure is:

(a) static pressure plus dynamic pressure

(b) static pressure minus dynamic pressure

(c) 1/2ρV2

(d) measured parallel to the local stream

2.

MULTIPLE CHOICE QUESTION

1 min • 1 pt

Which formula or equation describes the relationship between force (F), acceleration (a) and
mass (m)?

(a) a = F.m

(b) F = m/a

(c) F = m.a

(d) m = F.a

3.

MULTIPLE CHOICE QUESTION

1 min • 1 pt

If the continuity equation is applicable to an incompressible airflow in a tube at low subsonic speed, if the diameter of the tube increases the speed of the flow:

(a) increases

(b) becomes sonic

(c) decreases

(d) remains the same

4.

MULTIPLE CHOICE QUESTION

1 min • 1 pt

Static pressure acts:

(a) perpendicular to the direction of flow

(b) in the direction of the total pressure

(c) in all directions

(d) in the direction of the flow

5.

MULTIPLE CHOICE QUESTION

1 min • 1 pt

The units used to measure air density are:

(a) kg/cm3

(b) Bar

(c) kg/m3

(d) psi

6.

MULTIPLE CHOICE QUESTION

1 min • 1 pt

Bernoulli’s theorem states:

(a) dynamic pressure increases as static pressure increases

(b) dynamic pressure increases as static pressure decreases

(c) dynamic pressure is greatest at the stagnation point

(d) dynamic pressure is zero when the total pressure is greatest

7.

MULTIPLE CHOICE QUESTION

1 min • 1 pt

If the continuity equation is applicable to an incompressible airflow in a tube at low subsonic speed, if the diameter of the tube decreases the speed of the flow:

(a) increases

(b) becomes supersonic

(c) decreases

(d) remains the same

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CPD240 Mid S/64

The total pressure is:

Which formula or equation describes the relationship between force (F), acceleration (a) andmass (m)?

If the continuity equation is applicable to an incompressible airflow in a tube at low subsonic speed, if the diameter of the tube increases the speed of the flow:

Static pressure acts:

The units used to measure air density are:

Bernoulli’s theorem states:

If the continuity equation is applicable to an incompressible airflow in a tube at low subsonic speed, if the diameter of the tube decreases the speed of the flow:

If the velocity in a stream tube is increased, the streamlines:

The relative thickness of an aerofoil is expressed in:

The angle of attack of an aerofoil is the angle between the:

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Which formula or equation describes the relationship between force (F), acceleration (a) and
mass (m)?