POF T2

The lift force, acting on an aerofoil ==> wie ensteht Lift

An aeroplane in straight and level flight is subjected to a strong vertical gust. The point on the wing, where the instantaneous variation in wing lift effecrively acts is known as the: 

The C.P. of an aerofoil is:

WIng spolers are deflected symmetrically in flight in order to:

Upon extension of a winf spoiler, if the AOA remains constant?

upon wing spoiler etension in straight and level flight, if the speed and load factor remain constant

The most important problem of ice accretion on a transport aeroplane during flight is: 

which boundry layer, when considering its velocity profile perpendicular to the flow, has the greatest change in velocity close to the surface ? 

If ice present on the leading edge of teh wings, it may increase th eleading distance due to a higher V TH by as much as?

one important advanatge of a turbulent boundry layer has ober a laminar öayer is that the turbulent boundary layer:

Assuming constant IAS, when an aeroplane enters ground effect: 

1. effective AOA

2. induced Drag 

3. induced AOA 

The increased upwash experienced at the leading edge of a wing when trailing edge flaps are lowered causes:

If flaps are slightly asymmetric this would cause:

 When flaps are deployed at constant AoA the lift coefficient will

Compared with the clean configuration, the AoA at CLmax with trailing edge flaps extended is:

When (in flight) you lower the trailing edge flaps fully down:

A plain flap will increase CL max by:

 One of the main functions of flaps during an approach and landing is to:

The lift coefficient CL of a wing at a given AoA

 What must happen to the CL when flaps are deployed while maintaining a constant IAS in straight and lever flight?

 In order to maintain straight and lever flight at a constant airspeed, whilst the flaps are being retracted, the AoA will

A slotted flap will increase the CL max by:

If the increased downwash at the tail plane due to lowering trailing edge flaps is considered in isolation:

The contribution of the wing to the static longitudinal stability of an aeroplane:

For an aircraft in steady level flight, if the tail plane is producing a download, the CP of the wing must be:

The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:

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

The distance between the CG Datum and the CG Neutral Point in straight and level flight is called the:

For a statically stable aeroplane, the relationship between the neutral point and centre of gravity is such that the neutral point is located:

Long period (phugoid) oscillations are characterised by:

If an aeroplane has poor longitudinal stability in flight, what can be done to increase the stability?

The sum of the moments in flight are not zero, therefore movement would take place about:

Given an aeroplane in steady, straight and level flight at low speed and considering the effects of centre of gravity location and thrust, the highest value of wing lift occurs at:

 Which statement on dynamic longitudinal stability of a conventional aeroplane is correct

During a phugoid altitude varies xy  but during a short period oscillation it remains xy?

 If the static lateral stability of an aeroplane is increased, whilst its static directional stability remains constant:

The contribution of swept back wings to static directional stability:

 With increasing altitude and constant IAS the static lateral stability (i) and the dynamic lateral/directional stability (ii) of an aeroplane with swept back wing will:

 Which of these statements are correct or incorrect regarding a sideslip, with the relative airflow coming from the right, on an aeroplane that exhibits both directional and lateral stability? I. The initial tendency of the nose of the aeroplane is to move to the right. II. The initial tendency of the left wing is to move down.

To hold a given sideslip angle and airspeed, increased geometrical dihedral would: