ADMIX

Dihedral of a wing is the angle between:

wing plane and the horizontal with the aeroplane in an unbanked, level condition.

Taper ratio is the ratio of:

the root chord to the tip chord.

The aspect ratio of the wing is:

the ratio between the WING SPAN and the MEAN GEOMETRIC CHORD.

The Mean Aerodynamic Chord (MAC) for a given wing of any planform is

the chord of a rectangular untwisted wing with the same moment and lift.

The angle between the aeroplane longitudinal axis and the chord line is the

angle of incidicne.

An aerofoil is cambered when:

the line, which connects the centres of all inscribed circles, is curved.

A line connecting the leading- and trailing edge MIDWAY between the upper and lower surface o an aerofoil: This definiton is applicable for 

the camber line.

The relative thickness of an aerofoil is expressed in:

% chord.

The lift- and drag forces, acting on an aerofoil:

depend on the pressure around the aerofoil.

Lift is the component of the total aerodynamic force, perpendicular to the undisturbed airflow.

An aeroplane's angle of incidence is defined as the angle between the:

longitudinal axis and the wing root chord line.

statement about weight or mass:

The weight of a body can determined by multiplying its mass by the acceleration due to gravity.

statemant: Mass!

The mass of a body can be determined by dividing its weight by the acceleration due to gravity.

In the SI system the unit of measurement for weight is Newton.

Mass in the SI-System:

In the SI-System the unit of measurement for mass is the kilogramm.

Statements about weight or mass:

The mass of an object is independent of the acceleration due to gravity.

The weight of an object depends on the acceleration due to gravity.

In a tube:

an increase in the flow's temperature will decrease the mass flow.

Dihedral of a wing is the angle between:

the wing plane and the horizontal with the aeroplane in an unbanked, level condition.

Aspect Ratio of a wing is the ratio between:

wing span squared and wind area.

Wing sweep angle is the angle between:

the quarter-chord line of the wing and the lateral axis.

The mean geometric chord of a wing is the:

wing area divided by the wing span.

Statement S.P.:

As the angle of attack increases, the stagnation point on the wing's profile moves downwards.

The stagnation point is the point:

where the velocity of the relative airflow is reduced to zero.

If in a two-dimensional incompressible and subsonic flow, the streamlines converge the

static pressure in the flow will: decrease.

How are the speeds at point 1 and 2 related to the relative wind/airflow V?

When airflow over a wing becomes supersonic (Überschall), the pressure pattern on the top surface will become irregular.

The point where the aerodynamic lift acts on a wing is:

the centre of pressure.

The point where the single resultant aerodynamic force acts on an aerofoil, is called:

Centre of Pressure.

The location of the centre of pressure of a positively cambered aerofopil section at increasing

AoA will:

shift forward until approaching the critical angle of attack.

*approcahing = annähernd

Lowering the inboard flaps causes the wing centre of pressure:

to move inboard towards the wing root.

A pitch up could cause by:

forward movement of the C.P. (centre of pressure)

Assuming no flow seperation, when speed is decreased in straight and level flight on a positively cambered aerofoil, what happens to the:

I. centre of pressure?

II. the magnitude of the total lift force?

When speed increases in straight and level flight on a positively cambered aerofoil, what happens to the:

I. centre of pressure

II. magnitude of the total lift?

Assuming no flow effect and no compressibility effects the location of centre of pressure of a positively cambered aerofoil section:

Centre of pressure moves backwards when AoA decreases.

Assuming no flow seperation and no compressibility effects the location of the aerodynamic centre of an aerofoil section:

is independent of angle of attack.

Assuming no flow seperation and no compressibility effects the location of the centre of pressure of a symmetrical aerofoil section:

is at approximately 25% chord irrespective* of angle of attack.

*rücksichtslos

Assuming no flow seperation and no compressibility effects the location of the
centre of pressure of a symmetrical aerofoil section:

is independent of angle of attack.

The lift force acting on aerofoil:
(no flow seperation)

is mainly caused by suction* on the upperside of the aerofoil.

*Absaugung

Lift is generated when:

the flow dircetion of a certrain mass of air is changed.

correct statement about the CI and angle of attack:

for a symmetric aerofoil, if angle of attack = 0, CI = 0!