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The static pressure of gases work...

only in flow direction.

in all directions.

only in the direction of the total pressure.

only vertical to the flow direction.

Bernoulli's equation for frictionless, incompressible gases states that...

total pressure = dynamic pressure + static pressure.

dynamic pressure = total pressure + static pressure.

static pressure = total pressure + dynamic pressure.

total pressure = dynamic pressure - static pressure.

If surrounded by airflow (v>0), any arbitrarily shaped body produces...

lift without drag.

drag.

drag and lift.

constant drag at any speed.

Number 2 in the drawing corresponds to the...

profile thickness.

chord.

angle of attack.

chord line.

The angle (alpha) shown in the figure is referred to as...

lift angle.

angle of incidence.

angle of attack.

angle of inclination.

The ratio of span and mean chord length is referred to as...

aspect ratio.

trapezium shape.

wing sweep.

tapering.

Which point on the aerofoil is represented by number 1?

Transition point

Stagnation point

Center of pressure

Separation point

What pressure pattern can be observed at a lift-generating wing profile at positive angle of attack?

High pressure is created above, lower pressure below the profile

Pressure below remains unchanged, lower pressure is created above the profile

Low pressure is created above, higher pressure below the profile

Pressure above remains unchanged, higher pressure is created below the profile

The center of pressure is the theoretical point of origin of...

only the resulting total drag.

gravity forces of the profile.

all aerodynamic forces of the profile.

gravity and aerodynamic forces.

How do lift and drag change when approaching a stall condition?

Lift increases and drag decreases

Lift decreases and drag increases

Lift and drag decrease

Lift and drag increase

Pressure compensation on a wing occurs at the...

fuselage connections.

wing tips.

leading edge.

wing roots.

Which parts of an aircraft mainly affect the generation of induced drag?

the lower part of the gear.

the front part of the fuselage.

the outer part of the ailerons.

the wing tips.

Which effect does a decreasing airspeed have on the induced drag during a horizontal and stable cruise flight?

The induced drag will slightly decrease

The induced drag will increase

The induced drag will remain constant

The induced drag will collapse

When increasing the airflow speed by a factor of 2 while keeping all other parameters constant, how does the parasite drag change approximately?

It decreases by a factor of 4

It increases by a factor of 2

It increases by a factor of 4

It decreases by a factor of 2

Which statement about induced drag during the horizontal cruise flight is correct?

Induced drag increases with increasing airspeed

Induced drag has a minimum at a certain speed and increases at higher as well as lower speeds

Induced drag decreases with increasing airspeed

Induced drag has a maximum at a certain speed and decreases at higher as well as lower speeds

Which kinds of drag contribute to total drag?

Form drag, skin-friction drag, interference drag

Induced drag, form drag, skin-friction drag

Interference drag and parasite drag

Induced drag and parasite drag

What engine design at a Touring Motor Glider (TMG) results in least drag?

Engine and propeller mounted stowable on the fuselage

Engine and propeller mounted fix at the horizontal stabilizer

Engine and propeller mounted fix on the fuselage.

Engine and propeller mounted fix at the aircraft's nose

Pressure drag, interference drag and friction drag belong to the group of the...

main resistance.

total drag.

induced drag.

parasite drag.

How do induced drag and parasite drag change with increasing airspeed during a horizontal and stable cruise flight?

Induced drag decreases and parasite drag increases

Parasite drag decreases and induced drag increases

Parasite drag decreases and induced drag decreases

Induced drag increases and parasite drag increases

What is meant by "ground effect"?

Increase of lift and decrease of induced drag close to the ground

Increase of lift and increase of induced drag close to the ground

Decrease of lift and decrease of induced drag close to the ground

Decrease of lift and increase of induced drag close to the ground

Which statement concerning the angle of attack is correct?

A too large angle of attack may result in a loss of lift

The angle of attack is constant throughout the flight

The angle of attack cannot be negative

Increasing the angle of attack results in decreasing lift

The critical angle of attack...

is changed by different aircraft weights.

is not changed by different aircraft weights.

decreases with a rear centre of gravity.

increases with a front centre of gravity.

What leads to a decreased stall speed Vs (IAS)?

Higher load factor

Lower density

Decreasing weight

Lower altitude

Considering longitudinal stability, which C.G. position is most dangerous with a normal gliding plane?

Position beyond the front C.G. limit

Position beyond the rear C.G. limit

Position too far aside permissable C.G. limits.

Position far back within permissable C.G. limits

What can be said about the load factor (n) and the stall speed (Vs) in a co-ordinated turn?

n is lower than 1, Vs is higher than in straight and level flight.

n is lower than 1, Vs is lower than in straight and level flight.

n is larger than 1, Vs is higher than in straight and level flight.

n is larger than 1, Vs is lower than in straight and level flight.

Which option states a benefit of wing washout?

Structurally the wing is made more rigid against rotation

At high angles of attack the effectiveness of the aileron is retained as long as possible

Greater hardness because the wing can withstand more torsion forces

With the washout the form drag reduces at high speeds

In case of a stall it is important to...

increase the angle of attack and increase the speed.

increase the angle of attack and reduce the speed.

decrease the angle of attack and increase the speed.

increase the bank angle and reduce the speed.

Following a single-wing stall and pitch-down moment, how can a spin be prevented?

Deflect all rudders opposite to lower wing

Pulling the elevator to bring the plane back to normal attitude

Rudder opposite lower wing, releasing elevator to build up speed

Pushing the elevator to build up speed to re-attach airflow on wings

Which statement regarding a spin is correct?

During recovery the ailerons should be crossed

During the spin the speed constantly increases

During recovery the ailerons should be kept neutral

Only very old aeroplanes have a risk of spinning

The laminar boundary layer on the aerofoil is located between...

the stagnation point and the transition point.

the transition point and the separation point.

the stagnation point and the center of pressure.

the transition point and the center of pressure.

What types of boundary layers can be found on an aerofoil?

Laminar boundary layer along the complete upper surface with non-separated airflow

Turbulent layer at the leading wing areas, laminar boundary layer at the trailing areas

Turbulent boundary layer along the complete upper surface with separated airflow

Laminar layer at the leading wing areas, turbulent boundary layer at the trailing areas

With regard to the forces acting, how can stationary gliding be described?

The sum the air forces acts along with the lift force

The lift force compensates the drag force

The sum of air forces compensates the gravity force

The sum of air forces acts along the direction of air flow

What is the function of the horizontal tail (among other things)?

To initiate a curve around the vertical axis

To stabilise the aeroplane around the lateral axis

To stabilise the aeroplane around the longitudinal axis

To stabilise the aeroplane around the vertical axis

Stability around which axis is mainly influenced by the center of gravity's longitudinal position?

Lateral axis

Longitudinal axis

Gravity axis

Vertical axis

What structural item provides lateral stability to an airplane?

Elevator

Vertical tail

Wing dihedral

Differential aileron deflection

Which constructive feature is shown in the figure? See figure (PFA-006) L: Lift

Lateral stability by wing dihedral

Directional stability by lift generation

Differential aileron deflection

Longitudinal stability by wing dihedral

"Longitudinal stability" is referred to as stability around which axis?

Propeller axis

Lateral axis

Longitudinal axis

Vertical axis

The elevator moves an aeroplane around the...

elevator axis.

lateral axis.

vertical axis.

longitudinal axis.

Deflecting the rudder to the left causes...

yawing of the aircraft to the right.

pitching of the aircraft to the left.

pitching of the aircraft to the right.

yawing of the aircraft to the left.

What effect is referred to as "adverse yaw"?

Rudder operation results in a rolling moment to the opposite side due to more lift generated by the faster moving wing.

Aileron operation results in a yaw to the opposite side due to more drag at the down-deflected aileron

Aileron operation results in a yaw to the opposite side due to more drag at the up-deflected aileron

Aileron operation results in a yaw to the desired side due to less drag at the down-deflected aileron

SPL - Principles of Flight

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