Roman Eidia
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Quiz on Principles of flight. Part 2, created by Roman Eidia on 26/10/2018.

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Principles of flight. Part 2

Question 1 of 171

1

In which conditions, the density altitude is equal to the standard altitude accordirng to ISA ?

Select one of the following:

  • In The conditions which are equal with the table ISA.

  • In tropical conditions.

  • In the Arctic conditions.

  • When the standard height equals the height of the airport elevation.

Explanation

Question 2 of 171

1

In what proportion to the air density are depends aerodynamic forces on the aerofoil?

Select one of the following:

  • Proportionately

  • Inversely.

  • In proportion to the square of the density.

  • They are independent upon the air density.

Explanation

Question 3 of 171

1

W której grupie znajduje się urządzenie, które nie służy do zmniejszania sił, jakie pilot musi wywierać na drążek sterowy? In Which group that is device, which doesn't serve to reduce of the forces that the pilot to must execute on the control column?

Select one of the following:

  • Wyważenie masowe; - klapka wyważająca. Anti balance/ trim tab - Flettner.

  • Fletner; - trymer.Trim tab - Mass balance.

  • Wyważenie aerodynamiczne; - wyważenie sprężynowe. Aerodynamic balance- balance spring.

  • Wzmacniacz hydrauliczny; - klapka odciążająca. Hydraulic amplifier-Anti balance tab.

Explanation

Question 4 of 171

1

In normal flying conditions the controls forces are:

Select one of the following:

  • Always proportionally suitable to traffic changes or state of flight.

  • Always proportional suitable to the altitude and flight speed.

  • Independent from the flight speed.

  • Independent upon induced changes in movement or changes in flight.

Explanation

Question 5 of 171

1

In The profiles of normal, arcuate line-shaped frame, with an increase in angle of attack aerodynamic resultant force:

Select one of the following:

  • Moves forward along the chord.

  • Moves back along the chord.

  • For alpha<0 moves forward along the chord, and for alpha>0 moves along the chord to the rear.

  • Does not move along the chord.

Explanation

Question 6 of 171

1

In static profiles, with increased angle of attack aerodynamic resultant force:

Select one of the following:

  • Moves back along the chord.

  • For alpha<0 moves forward along the chord, and for alpha>0 moves along the chord to the rear.

  • Does not move along the chord.

  • Moves forward along the chord.

Explanation

Question 7 of 171

1

In the symmetric profiles for the angle of attack alpha = 0 °:

Select one of the following:

  • The geometric chord of the profile chord coincides with an aerodynamic profile.

  • The geometric chord of the profile does not match the profile aerodynamic chord.

  • Geometric chord of the profile coincides with the aerodynamic mean chord other Profile

  • Geometric chord of the profile does not coincide with the aerodynamic mean chord of the profile.

Explanation

Question 8 of 171

1

In the profiles of symmetric, with an increase in angle of attack aerodynamic resultant force:

Select one of the following:

  • Does not move along the chord.

  • Moves forward along the chord.

  • Moves back along the chord.

  • For alpha<0 moves forward along the chord, and for alpha> 0 moves along the chord to the rear.

Explanation

Question 9 of 171

1

W rozwiązaniu konwencjonalnym usterzenie pionowe składa się z: In the conventional solution, vertical tail Ionsists of:

Select one of the following:

  • Statecznika pionowego stanowiącego przednią, nieruchomą część-steru kierunku stanowiącego tylną ruchomą część. Vertical stabilizer being the front immovable part of a direction rudder which is the rear movable part.

  • Statecznika pionowego stanowiącego przednią, nieruchomą część-steru wysokości stanowiącego tylną ruchomą część. Vertical stabilizer beint the from immovable part of a height rudder - being the back movable part.

  • Statecznika pionowego stanowiącego tylną, nieruchomą część-steru kierunku stanowiącego przednią ruchomą część. Vertical stbilizer as rear immovable part of the directional rudder being the front movable part.

  • Statecznika pionowego stanowiącego przednią, ruchomą część-steru kierunku stanowiącego tylną nieruchomą część. Vertical stabilizer as front movable part of the directional rudder being rear immovable part.

Explanation

Question 10 of 171

1

W rozwiązaniu konwencjonalnym usterzenie wysokości składa się z: In the conventional solution the height tail consists of:

Select one of the following:

  • Statecznika poziomego stanowiącego przednią, nieruchomą część-steru wysokości stanowiącego tylną ruchomą część. Tail-plane horizontal stabilizer as the front immovable part of the height rudder being the front movable part.

  • Statecznika pionowego stanowiącego przednią, nieruchomą część-steru wysokości stanowiącego tylną ruchomą część. Vertical stabilizer as front immovable part of the directional rudder being the rear movable part.

  • Statecznika poziomego stanowiącego tylną, nieruchomą część-steru wysokości stanowiącego przednią ruchomą część. Horizontal stabilizer as rear immovable part of the directional rudder being the front movable part.

  • Statecznika poziomego stanowiącego przednią, ruchomą część-steru wysokości stanowiącego tylną nieruchomą część. Horizontal stabilizer being the front movable part of the height rudder as the rear immovable part.

Explanation

Question 11 of 171

1

The coordinate system describing the movement of the aircraft during flight axis OX? Is called:

Select one of the following:

  • Longitudinal axis.

  • Lateral axis.

  • The vertical axis.

  • Horizontal axis.

Explanation

Question 12 of 171

1

The coordinate system describing the movement of the aircraft during flight axis OY? Is called:

Select one of the following:

  • Lateral axis.

  • The vertical axis.

  • Horizontal axis.

  • Longitudinal axis.

Explanation

Question 13 of 171

1

The coordinate system describing the movement of the aircraft during flight axis OZ? Is called:

Select one of the following:

  • The vertical axis.

  • Horizontal axis.

  • Longitudinal axis.

  • Lateral axis.

Explanation

Question 14 of 171

1

In the flight, the pilot set tilts a joystick to the right. Assuming that the aileron deflects by the same angle, following statement will be true:

Select one of the following:

  • Drag force on an airleron going-down will be greater than the drag force on the second one.

  • Drag force on an airleron going-down will be lower than the drag force on the second one.

  • Drag forces on both ailerons will increase by the same value.

  • The drag force on both ailerons will decrease by the same value.

Explanation

Question 15 of 171

1

In a result of aileron going up and down by the same angle will be:

Select one of the following:

  • Unfavorable ailerons drag moment.

  • Positive ailerons drag moment.

  • Unfavorable roll moment.

  • Positive yaw moment.

Explanation

Question 16 of 171

1

Using of winglets on tips of wings decrease drag:

Select one of the following:

  • Induced.

  • Interference.

  • Shape.

  • Slot.

Explanation

Question 17 of 171

1

A boundary layer of an aerofoil is a layer in which:

Select one of the following:

  • The speed of air molecules is less than the velocity of airflow.

  • There is a transition of turbulent to the laminar airflow.

  • An airflow has a laminar characteristic.

  • An airflow has a turbulent characteristic.

Explanation

Question 18 of 171

1

The value of the coefficient of lift (CL) for the critical angle of attack "AOA" has the maximum value.

Select one of the following:

  • It is always true.

  • It is always false.

  • It is true only for symmetric profiles.

  • It is false only for symmetric profiles.

Explanation

Question 19 of 171

1

The value of the coefficient of drag (Cd) for the critical angle of attack "AOA" has the maximum value.

Select one of the following:

  • It is always false.

  • It is always true.

  • It is true only for symmetric profiles.

  • It is false only for symmetric profiles.

Explanation

Question 20 of 171

1

Wewnętrzna kompensacja aerodynamiczna steru odbywa się poprzez zastosowanie: The internal aerodynamic balance of aileron is executed by:

Select one of the following:

  • Przepony, która jednocześnie zmniejsza opór szczelinowy. Hinged balance panel, which also reduces drag of slots.

  • Dodatkowej powierzchni sterowej przed osią obrotu steru. Additional steering surface before pivot of control.

  • Klapki dociążającej. Anti balance tab.

  • Klapki odciążającej. Flettner tab.

Explanation

Question 21 of 171

1

With increase of altitude an air density:

Select one of the following:

  • Always decreases.

  • Always grows.

  • Does not change.

  • Decreases- if the temperature decreases and increases- if the temperature rises.

Explanation

Question 22 of 171

1

The Load factor 'n ' during dive is:

Select one of the following:

  • n=0 .

  • n<0.

  • n>0.

  • n=1.

Explanation

Question 23 of 171

1

The load factor during turn depends from:

Select one of the following:

  • Bank Angle and airspeed.

  • An airspeed.

  • The volume of drag.

  • Induced drag.

Explanation

Question 24 of 171

1

Moving of whose devices are not mechanically coupled with moving control surface?

Select one of the following:

  • Trimmer tab.

  • Flettner.

  • Anti balance tab.

  • Ballance tab.

Explanation

Question 25 of 171

1

Wykres zależności Cx = f(alpha;) dla profilu symetrycznego jest: A graph of function of the coeficient of drag Cd = f (AOA) for asymmetric profile is:

Select one of the following:

  • Symetryczny względem osi "Cx". Symmetrical to the axis of "Cd".

  • Symetryczny względem osi alpha. Symmetrical to the axis "AOA".

  • Symetryczny względem środka układu współrzędnych.Symmetrical to the center of the coordinate system.

  • Nie posiada żadnej symetrii. It has no symmetry.

Explanation

Question 26 of 171

1

Wykres zależności Cz = f(Cx) dla profilu symetrycznego jest: A graph of the function Cl = f (Cd) for the symmetric profile is:

Select one of the following:

  • Symetryczny względem osi "Cx". Symmetrical to the axis of "Cx".

  • Symetryczny względem osi "Cz". Symmetrical to the axis of "Cl".

  • Symetryczny względem środka układu współrzędnych. Symmetrical towards the center of the coordinate system.

  • Nie posiada żadnej symetrii. It has no symmetry.

Explanation

Question 27 of 171

1

Wykres zależności Cz = f(Cx) wykonany na podstawie pomiarów w czasie lotu nazywamy: A graph of the function Cl = f (Cd) made up on of the basic measurements during a flight, is called:

Select one of the following:

  • Biegunową szybowca. A polar curve.

  • Biegunową prędkości szybowca. A polar of glider speed.

  • Biegunową profilu. A polar of profile.

  • Biegunową skrzydła. A polar of wing.

Explanation

Question 28 of 171

1

Wykres zależności Cz = f(alpha;) dla profilu symetrycznego jest: A graph of the function Cl = f (AOA) for a symmetric profile is:

Select one of the following:

  • Symetryczny względem środka układu współrzędnych. Symmetrical to the center of the coordinate system.

  • Symetryczny względem osi "alpha". Symmetrical to the 'AOA' axis.

  • Symetryczny względem osi "Cz". Symmetrical to the Cl axis.

  • Nie posiada żadnej symetrii. It has no symmetry.

Explanation

Question 29 of 171

1

Wykresy jakich zależności dla profilu symetrycznego przechodzą przez środek układu współrzędnych? Graphs of which functions for the symetric profile are intersecting the center of the coordinate system?

Select one of the following:

  • Cz = f(alpha), Cm = f(alpha). Cl = f (AOA), Cm = f (AOA).

  • Cz = f(alpha), Cx = f(alpha). Cl = f (AOA), Cd = f (AOA).

  • Cx = f(alpha), Cm = f(alpha). Cd = f (AOA), Cm = f (AOA).

  • Cz = f(alpha), Cz = f(Cx). Cl = f (AOA), Cl = f (Cd).

Explanation

Question 30 of 171

1

Wykresy jakich zależności dla profilu symetrycznego są osiowosymetryczne? Graphs of which functions for the symetric profile are intersect center of coordinate system?

Select one of the following:

  • Cx = f(alpha), Cz = f(Cx). Cl = f(AOA), Cl = f(Cd).

  • Tylko Cx = f(alpha). Only Cd = f(AOA).

  • Cz = f(alpha), Cx = f(alpha). Cl = f(AOA), Cd = f(AOA).

  • Tylko Cz = f(Cx). Only Cl = f(Cl).

Explanation

Question 31 of 171

1

Dihedral of the wings is used to:

Select one of the following:

  • Increase of the lateral stability of the glider.

  • Increase the max=L/D of a glider.

  • Improve of lateral maneuverability of a glider.

  • Reduce of the induced drag of a glider.

Explanation

Question 32 of 171

1

The increase in air temperature at a constant altitude causes:

Select one of the following:

  • Reduction in air density.

  • Increase in air density.

  • Does not change the density and relative humidity.

  • Increase in relative humidity.

Explanation

Question 33 of 171

1

Z jakich głównych elementów powstaje opór statku powietrznego zwany „szkodliwym”? What are the main elements of the resistance aircraft called skin friction dran?

Select one of the following:

  • Z „oporu kształtu” bryły statku powietrznego i z „oporu tarcia” powietrza o powierzchnię tej bryły. The "resistance form" body of the aircraft and the "frictional resistance of air on the surface of this body.

  • Z lepkości powietrza i z oporów wirów powstających na bryle statku. The viscosity of the air and eddies of emerging resistance to block the vessel.

  • Z „oporu kształtu” bryły statku powietrznego i z „oporu indukowanego” powstającego na powierzchni bryły statku. The "resistance form" solid aircraft, and "induced drag" formed on the surface of a solid board.

  • Z „oporu tarcia” powietrza o powierzchnię bryły statku powietrznego i z „oporu interferencyjnego”. "Frictional resistance of air on the solid surface of the aircraft and the" resistance interference ".

Explanation

Question 34 of 171

1

The principle of continuity of the movement of air flowing through the tunnel with variable cross-section states that:

Select one of the following:

  • If the cross-section of the tunnel grow twice, the air speed decreases twice.

  • If the cross-section of the tunnel grow twice, the air velocity increases twice.

  • If the cross-section of the tunnel grow twice, the air velocity decreases fourfold.

  • If the cross-section of the tunnel grow twice, the air velocity increases fourfold.

Explanation

Question 35 of 171

1

Apply of aerodynamic balance of controls is designed to:

Select one of the following:

  • Reduce the hinge moment.

  • Increase the hinge moment.

  • Balance of control surface in neutral position.

  • Mass balance of control surface.

Explanation

Question 36 of 171

1

Zdolność do zachowania stanu równowagi i przeciwdziałania jego zmianom nazywamy: The ability to maintain the balance and prevent its changes is called:

Select one of the following:

  • Statecznością statyczną. The static stability.

  • Statecznością dynamiczną. The dynamic stability.

  • Stabilnością statyczną. The static stability.

  • sterownością dynamiczną dynamic steering.

Explanation

Question 37 of 171

1

Ability to change the steady-state flight under the influence of corresponding rudder deflection is called:

Select one of the following:

  • Steering

  • The static stability.

  • The dynamic stability.

  • The stability.

Explanation

Question 38 of 171

1

Zewnętrzna kompensacja aerodynamiczna steru odbywa się poprzez zastosowanie: The external aerodynamic compensation of control surface takes place by the application of:

Select one of the following:

  • Dodatkowej powierzchni sterowej przed osią obrotu steru. An additional control surface before of the control hinge line.

  • Klapki dociążającej. The anti balance tab.

  • Klapki odciążającej.The balance tab.

  • Flettnera. The flettner.

Explanation

Question 39 of 171

1

The phenomenon of aileron reversal that is:

Select one of the following:

  • A twisting the wing due to aileron deflection.

  • The formation of initial vibration.

  • A buffeting formation.

  • A coupling of the ailerons.

Explanation

Question 40 of 171

1

Reducing of airstream cross- section means:

Select one of the following:

  • A drop of static pressure in the stream and speed increase.

  • Increase of static pressure in the stream and speed drop.

  • Stagnation of stream velocity.

  • Increase in streamline of the pressure stream.

Explanation

Question 41 of 171

1

Zwichrzenie aerodynamiczne skrzydła charakteryzuje się tym, że: An aerodynamic twist of wing is characterized itself by:

Select one of the following:

  • Zwichrzenie aerodynamiczne skrzydła charakteryzuje się tym, że: Appliance on tips of the wings aerodynamic profiles for which detach of air flow for Stall angle of attack is less intense.

  • Cięciwy profilów geometrycznych w kolejnych przekrojach nie leżą w jednej płaszczyźnie. The chords of next air profiles are not in the same plain.

  • Skrzydła wygięte są w dół podczas postoju szybowca na ziemi. The wings are deflect donward when glider is on the ground.

  • Skrzydła wygięte są w górę podczas lotu. The wings are deflected upward in the flight.

Explanation

Question 42 of 171

1

Zwichrzenie geometryczne skrzydła charakteryzuje się tym, że: The geometrical twist of wings is characterized itself by:

Select one of the following:

  • Cięciwy profili geometrycznych w kolejnych przekrojach nie leżą w jednej płaszczyźnie. profiling geometric chord in subsequent sections do not lie in one line

  • skrzydła wygięte są w dół podczas postoju szybowca na ziemi the wings are bent down when parked glider on the ground

  • skrzydła wygięte są w górę podczas lotu wings are bent upwards in the flight

  • na końcówkach skrzydeł stosuje się profile, na których oderwanie strug dla &alpha;kryt jest mniej intensywne on the wingtip sections profile are applied where the plane separation is less intense

Explanation

Question 43 of 171

1

Increasing the lift on the wing causes a change in the induced drag:

Select one of the following:

  • Greater.

  • Less.

  • It has no effect on induced drag.

  • Smaller or greater depending from the speed of flight.

Explanation

Question 44 of 171

1

Zwiększanie kąta natarcia alpha>alpha kr. powoduje: Increasing the angle of attack alpha > alpha cr causes:

Select one of the following:

  • Zwiększanie "Cx" oraz zmniejszanie "Cz" . Increasing the "Cx" and reducing the "Cz".

  • Zwiększanie "Cz" oraz zmniejszanie "Cx".Increasing the "Cz", and reducing the "Cx".

  • Zwiększanie "Cx" oraz "Cz". Increasing the "Cx" and "Cz".

  • Zmniejszanie "Cx" oraz "Cz". Reducing the "Cx" and "Cz".

Explanation

Question 45 of 171

1

What kind of rule is? "In the tunnel by which an air flows a product of cross-sectional area and an air velocity is constant S * v = const"

Select one of the following:

  • The Equation of Continuity.

  • The Bernoulli's principle.

  • The Bernoulli Principles.

  • The moment of momentum principle.

Explanation

Question 46 of 171

1

Co to za zasada?: „W tunelu, przez który przepływa powietrze, suma ciśnienia statycznego i dynamicznego jest stała w każdym punkcie tego przepływu” What kind of rule is? "In the tunnel by which an air flows, the sum of static and dynamic pressure is constant at every point of the movement"

Select one of the following:

  • prawo Bernouli’ego the Bernouli right B

  • zasada ciągłości ruchu the principle of movement continuity

  • zasada zachowania energii przepływu the principle of conservation of energy flow

  • zasada zachowania ciśnienia przepływu zamkniętego the principle of conservation of closedflow pressure

Explanation

Question 47 of 171

1

Dla opisania ruchów statku powietrznego (samolotu, śmigłowca, szybowca etc) w przestrzeni stosowany jest układ osi współrzędnych x-y-z. Jakie oznaczenie nosi oś pionowa? To describe the movements of aircraft (airplane, helicopter, glider, etc.) in the space system is used three axes. How the vertical axis is marked?

Select one of the following:

  • z. Normal axis.

  • X. Longitudal axis.

  • Y. Lateral axis.

  • Dowolne. On discretion.

Explanation

Question 48 of 171

1

Dla opisania ruchów statku powietrznego (samolotu, śmigłowca, szybowca etc) w przestrzeni stosowany jest układ osi współrzędnych x-y-z. Jakie oznaczenie nosi oś podłużna? To describe the movements of aircraft (airplane, helicopter, glider, etc.) in the space system iaxes xyz is used. How the longitudinal axis is marked?

Select one of the following:

  • X. Longitudal axis.

  • Y. Lateral axis.

  • Z. Normal axis.

  • There is no marking.

Explanation

Question 49 of 171

1

To describe the movements of aircraft (airplane, helicopter, glider, etc.) in the space system axes xyz is used. How is the transverse axis marked?

Select one of the following:

  • Y. Lateral axis.

  • X. Longitudal axis.

  • Z. Normal axis.

  • On discretion.

Explanation

Question 50 of 171

1

When air flows through the channel of variable cross-sectional area the static pressure changes. How?

Select one of the following:

  • Decreases with decreasing cross-sectional area.

  • Decreases with increasing cross-sectional area.

  • Does not change at all.

  • Increases with reducing cross-sectional area.

Explanation

Question 51 of 171

1

How does an object behave (aircraft, helicopter, glider, hang-gliding, etc.) dynamically unstable after it has been balanced off?

Select one of the following:

  • The object moves, mostly harmonic, with increasing amplitude.

  • The object moves, the most often harmonic with damped oscilaion.

  • It remains the position after being balanced off.

  • It takes the position more distant from the balance position.

Explanation

Question 52 of 171

1

How does the object behave (aircraft, helicopter, glider, hang-gliding, etc.) dynamically stable being balanced off?

Select one of the following:

  • The object moves, most often harmonic, with damped oscilation.

  • It maintains the position wich it has reached after being balanced off.

  • Performing movement, most often harmonic, with divergent oscilation.

  • Immediately after the termination of the pulse precipitation returns to the balanced position.

Explanation

Question 53 of 171

1

How does the harmful drag behaved when increasing air speed?

Select one of the following:

  • Increases with the square of speed.

  • Remains constant.

  • Decreases proporconalnie to the inverse of speed.

  • Swinging.

Explanation

Question 54 of 171

1

How does the harmful drag behaved when increasing air speed?

Select one of the following:

  • The resistance increases with the square of speed.

  • The resistance remains constant.

  • The resistance decreases proportionally to the inverse of speed.

  • The resistance varies.

Explanation

Question 55 of 171

1

How will change the centrifugal force with the same speed of flight in the turn if the radious will be decrease itself?

Select one of the following:

  • Will increase.

  • Will decrease.

  • Remain unchanged.

  • Will decrease to zero.

Explanation

Question 56 of 171

1

How will change the centrifugal force with the same speed of flight in the turn if the radious will be decrease itself?

Select one of the following:

  • The centrifugal force increases.

  • The centrifugal force will decrease.

  • The centrifugal force will remain unchanged.

  • The centrifugal force will decrease to zero.

Explanation

Question 57 of 171

1

The angle of climb "gamma" on a constant angle of attack "alpha" during growth of altitude:

Select one of the following:

  • Remains unchange.

  • Increases.

  • Decreases.

  • Changes and it can be readed by drawing of the glider polar.

Explanation

Question 58 of 171

1

Lot odbywa się na kącie natarcia, dla którego współczynnik siły oporu Cx ma wartość minimalną: alpha=alpha(Cxmin). W wyniku niewielkiego zwiększenia kąta natarcia: Flight takes place on the angle of attack, for which the drag coefficient Cd has the minimum of value: alpha=alpha(Cdmin). In a result of a small increase of angle of attack:

Select one of the following:

  • Stosunek Cz/Cx wzrośnie. Maximum ratio Cl/Cd will increase.

  • Stosunek Cz/Cx zmaleje. Maximum ratio Cl/Cd will decrease.

  • Stosunek Cz/Cx nie zmieni się. Maximum ratio Cl/Cd will not change.

  • Doskonałość płatowca nie zmieni się. Maximum ratio Cl/Cd of the airframe will decreases.

Explanation

Question 59 of 171

1

Lot odbywa się na kącie natarcia, dla którego współczynnik siły oporu Cx ma wartość minimalną: alpha=alpha(Cxmin). W wyniku niewielkiego zwiększenia kąta natarcia: Flight takes place on the angle of attack, for which the drag coefficient Cd has the minimum of value: alpha=alpha(Cdmin). In a result of a small increase of angle of attack:

Select one of the following:

  • Doskonałość płatowca wzrośnie. Maximum ratio of airframe Cl/Cd will increase.

  • Doskonałość płatowca zmaleje. Maximum ratio of airframe Cl/Cd will decrease.

  • Doskonałość płatowca nie zmieni się. Maximum ratio of airframe Cl/Cd will not change.

  • Stosunek Cz/Cx zmaleje. Maximum ratio Cl/Cd will decrease.

Explanation

Question 60 of 171

1

Main type of spin is influenced by the following factors:

Select one of the following:

  • Glider's center of gravity, the glider mass-distribution, location and size of the empennage.

  • Glider's center of gravity, the glider mass-distribution, setting of trim tabs.

  • Distribution of the glider masses - setting of the trim tabs, location and size of the empennage.

  • Setting of the trim tabs, glider's center of gravity, location and size of the empennage.

Explanation

Question 61 of 171

1

To recover of the plane from of skidding during the turn and make the correct turn to do perform:

Select one of the following:

  • To increase angle of bank or use rudder to increase of turn radious.

  • To reduce angle of bank or decrease of turn angle radious.

  • Increase angle of bank or to increase the angular velocity of the turn.

  • Reduce the bank or increase the angular velocity of the turn.

Explanation

Question 62 of 171

1

Aby wyprowadzić samolot z ześlizgu w zakręcie i wykonać zakręt prawidłowy należy: To recover of the plane from of the slliping during the turn and make the correct turn to do perform:

Select one of the following:

  • Zmniejszyć przechylenie lub zwiększyć prędkość kątową zakrętu. To reduce the angle of bank or use rudder to decrease of turn radious.

  • Zwiększyć przechylenie lub zwiększyć prędkość kątową zakrętu. Increase the pitch of turn.

  • Zmniejszyć przechylenie lub zmniejszyć prędkość kątową zakrętu. Increase the pitch of turn.

  • Zwiększyć przechylenie lub zmniejszyć prędkość kątową zakrętu. Increase angular roll or increase the bank.

Explanation

Question 63 of 171

1

What is that rule? "In the tunnel through which air flows and cross-product of the air velocity is constant S * v = const

Select one of the following:

  • The Equation of Continuity.

  • Bernouli principle.

  • The Bernoulli's law.

  • The principle of conservation of momentum.

Explanation

Question 64 of 171

1

What kind is that rule? In the tunnel by which air flows, the product of static and dynamic pressure is constant in each point of airflow.

Select one of the following:

  • The Bernoulli's principle.

  • The Equation of contuity principle.

  • The principle of conservation of energy flow.

  • The principle of conservation of closed-flow pressure

Explanation

Question 65 of 171

1

Does is between the steering and stability of a flying object (plane, helicopter, glider etc.) some relation to each other?

Select one of the following:

  • They operate against to each other.

  • They coopoperate.

  • There is no relationship between them.

  • Stability supported a longitudinal steering.

Explanation

Question 66 of 171

1

Does a proppeler efficiency (eta)"h" for the fixed propeller can take the value zero? If yes, in what circumstances?

Select one of the following:

  • The propeller has RPM and the airplane has a speed TAS = 0 or TAS is so large that it don't gives any Thrust.

  • Only when the propeller has RPM and the airplane has a TAS = 0.

  • Only when TAS is so large that Thrust is 0.

  • (ETA) "h" can not take a zero value.

Explanation

Question 67 of 171

1

When an air flows by the stream tube with variable changed cross-sectional area the static pressure changes itself. How?

Select one of the following:

  • Decreases with the reduction of the crosssectional area.

  • Decreases with increasing cross-sectional area.

  • Does not change at all.

  • Increases with the reduction of cross-sectional area.

Explanation

Question 68 of 171

1

How does the object behave (aircraft, helicopter, hang-gliding, etc.) dynamically unstable after being balanced off?

Select one of the following:

  • The object moves, mostly harmonic, with increasing amplitude.

  • The object moves, mostly harmonic, with decreasing amplitude.

  • It remains the position after being balnced off .

  • It takes the position more and more distant from the balanced position.

Explanation

Question 69 of 171

1

How does the object behave (aircraft, helicopter, hang-gliding, etc.) dynamically stable after being balanced off?

Select one of the following:

  • The object moves, most often harmonic, with decreasing amplitude.

  • It maintains the position it reached after being balanced off .

  • Performs the movement, mostly harmonic, with increasing amplitude.

  • Immediately after the termination of the pulse precipitation returns to the balanced position.

Explanation

Question 70 of 171

1

How does harmful resistance behave with increased flight speed?

Select one of the following:

  • Increases with the square of speed.

  • Remains constant.

  • Decreases in proportion to the inverse of speed.

  • Swing.

Explanation

Question 71 of 171

1

How does is harmful resistance behave with increased flight speed?

Select one of the following:

  • The drag increases with the square of speed.

  • The drag remains constant.

  • The drag decreases proportionally to the inverse of speed.

  • The drag swing.

Explanation

Question 72 of 171

1

How will the centrifugal force change during turn with the same speed if radius of turn will be reduced?

Select one of the following:

  • Increase itself.

  • Decrease itself.

  • Remain unchanged.

  • Decrease itself to zero.

Explanation

Question 73 of 171

1

How will the centrifugal force change if (at the same linear speed) you decrease the radius?

Select one of the following:

  • It will increase.

  • It will decrease.

  • It will remain unchanged.

  • It will decrease to zero.

Explanation

Question 74 of 171

1

How does the minimum speed and maximum level flight speed change with increasing altitude?

Select one of the following:

  • Vmin increases / Vmax decreases.

  • Vmin increases / Vmax increases.

  • Vmin decreases / Vmax decreases.

  • Vmin decreases / Vmax increases.

Explanation

Question 75 of 171

1

What changes in the arcraft attitude are be responsible for creation of the giroscopic moment of powerplant?

Select one of the following:

  • Pitch, yaw.

  • Pitch, roll.

  • Yaw, roll.

  • Acceleration- braking.

Explanation

Question 76 of 171

1

If the wing autorotation is not stopped by the pilot:

Select one of the following:

  • The airplane will automatically go into the flight phase called spin.

  • The airplane will automatically go into the flight phase called static stall.

  • The airplane will automatically go into the flight phase called dynamic stall.

  • The airplane wili automatically go into the flight phase called spiral.

Explanation

Question 77 of 171

1

If the advance ratio increases:

Select one of the following:

  • Angles of attack of individual prop blade sections decrease.

  • Angles of attack of individual prop blade sections increase.

  • Angles of attack of individual prop blade sections decreasedoes not change.

  • Angles of attack of individual prop blade sections reach critical values.

Explanation

Question 78 of 171

1

If the aircraft center of gravity coincides with the neutral point:

Select one of the following:

  • The airplane is neither stable nor unstable.

  • The airplane is stable.

  • The airplane is unstable.

  • The airplane is uncontrollable.

Explanation

Question 79 of 171

1

If the center of gravity of the airplane with a cambered aerofoil is placed forward of the neutral point:

Select one of the following:

  • The airplane is stable.

  • The airplane is unstable.

  • The airplane is statically neutral.

  • The airplane is neither stable nor notunstable.

Explanation

Question 80 of 171

1

If the center of gravity of the airplane with a cambered aerofoil is placed aft of the neutral balance center:

Select one of the following:

  • The airplane is unstable.

  • The airplane is not steering.

  • The airplane is stable.

  • The airplane is neither stable nor unstable.

Explanation

Question 81 of 171

1

If the speed of flight is significantly increased (fixed pitch propeller):

Select one of the following:

  • Blade angle of attack decreases.

  • Blade angle of attack increases slightly.

  • Blade angle of attack does not change.

  • Blade angle of attack increases substantially.

Explanation

Question 82 of 171

1

If the RPM of the fixed pitch propeller is significantly incrased:

Select one of the following:

  • Blade angle of attack increases.

  • Blade angle of attack decreases slightly.

  • Blade angle of attack does not change.

  • Blade angle of attack considerably decrease.

Explanation

Question 83 of 171

1

Angles of attack of individual propeller sections reach a negative value:

Select one of the following:

  • If the advance ratio is sufficiently large.

  • If the advance ratio is negative.

  • If the advance ratio equals zero.

  • If the advance ratio equals one.

Explanation

Question 84 of 171

1

When is the blade angle of attack alpha = 0°?

Select one of the following:

  • When the propeller slip = 0.

  • When the airplane speed = 0.

  • When the effective propeller pitch propeller = 0.

  • Never.

Explanation

Question 85 of 171

1

When does the slip of the fixed pitch propeller in a GA airplane equals the geometric pitch?

Select one of the following:

  • When the airplane speed = 0.

  • When the blade angle of attack = 0°.

  • Never.

  • When the advance ratio = 1.

Explanation

Question 86 of 171

1

When does the slip of the fixed pitch propeller in a GA airplane equals zero?

Select one of the following:

  • When the blade angle of attack = 0°.

  • Never.

  • When the advance ratio = 0.

  • When the airplane speed = 0.

Explanation

Question 87 of 171

1

When does the geometric pitch of a fixed pitch propeller in a GA aeroplane equals the effective pitch?

Select one of the following:

  • When the blade angle of attack = 0°.

  • When the airplane speed = 0.

  • Never.

  • When the advance ratio = 0.

Explanation

Question 88 of 171

1

When does the geometric pitch of a fixed pitch propeller in a GA aeroplane equals zero?

Select one of the following:

  • Never.

  • When the advance ratio = 0.

  • When the airplane speed = 0.

  • When the blade angle od attack = 0°.

Explanation

Question 89 of 171

1

When does the effective pitch of a fixed pitch propeller in a GA aeroplane equal zero?

Select one of the following:

  • When the airplane speed = 0.

  • When the blade angle of attack = 0°.

  • Never.

  • When the advance ratio = 1.

Explanation

Question 90 of 171

1

Which of the following changes is not caused by an increase in the engine thrust?

Select one of the following:

  • A change the aileron hinge moment.

  • A change in a pitch-down moment.

  • A change in angle of attack of the horizontal tailplane.

  • A sudden change in the horizontal tailplane airflow speed.

Explanation

Question 91 of 171

1

Wich design feature is not meant to compensate for the slipstream effect?

Select one of the following:

  • Rudder aerodynamic compensation.

  • Fixed rudder balance tab.

  • Rudder offset.

  • Asymmetrical profile of the rudder.

Explanation

Question 92 of 171

1

Which description fits the physical unit called "available power"?

Select one of the following:

  • The ratio of work done to the time it's been done within - unit Watt [W].

  • The product of the work done and time it's been done within - unit Watt [W].

  • The ratio of work done to the time it's been done within - unit joule [J].

  • The product of work done and the time it's been done within - unit joule [J].

Explanation

Question 93 of 171

1

Which description of the physical quantity characterizes the work done?

Select one of the following:

  • The product of force and distance - joule [J].

  • The ratio of force to distance - joule [J].

  • The product of force and distance - Watt [W].

  • The ratio of force to distance - Watt [W].

Explanation

Question 94 of 171

1

A plane is flown at an angle of attack, for which the drag coefficient CD is at its minimum. As a result of a slight increase of the angle of attack:

Select one of the following:

  • The ratio CL / CD increases.

  • The ratio CL / CD decreases.

  • The ratio CL / CD does not change.

  • The airframe glide ratio does not change.

Explanation

Question 95 of 171

1

A plane is flown at an angle of attack, for which the drag coefficient CD is at its minimum. As a result of a slight increase of the angle of attack:

Select one of the following:

  • The airframe glide ratio increases.

  • The airframe glide ratio decreases.

  • The airframe glide ratio does not change.

  • The ratio CL / CD decreases.

Explanation

Question 96 of 171

1

The measure of static stability is a derivative of Mx = dM / dx, called the "time derivative of M with respect to variable x". What value of the derivative determines instability?

Select one of the following:

  • A positive (+).

  • Negative (-).

  • The mark does not matter.

  • Depends on the variable x.

Explanation

Question 97 of 171

1

Eccentricity (decentralization) of the propeller means that:

Select one of the following:

  • The propeller thrust vector axis does not go through the airplane's center of gravity

  • The propeller thrust vector axis does not go through the airplane's engine shaft center.

  • The propeller thrust vector axis does not go through the airplane's center of pressure.

  • The propeller thrust vector axis does not go through the airplane's geometric center.

Explanation

Question 98 of 171

1

Eccentricity (decentration)of the propeller:

Select one of the following:

  • Causes changes in the yawing and/or pitching moments.

  • Causes changes in the aircraft rolling moments.

  • Causes changes in the lateral plane balancing.

  • Does not cause any significant changes affecting the controlability of the airplane.

Explanation

Question 99 of 171

1

The engine gyroscopic moment disappears when the following ceases:

Select one of the following:

  • The angular velocity of changes.

  • The angular acceleration of changes.

  • The centripetal acceleration of changes.

  • The centrifugal acceleration of changes.

Explanation

Question 100 of 171

1

The yawing moment that is caused by the aerodynamic force acting on the vertical fin due to an asymmetric airflow behind the propeller is called:

Select one of the following:

  • Slipstream effect.

  • Drag moment.

  • Giroscopic moment.

  • Eccentric moment.

Explanation

Question 101 of 171

1

At low airplane speed the highest propeller efficiency is achieved:

Select one of the following:

  • With low geometric pitch.

  • With high geometric pitch.

  • With low effectivepitch.

  • With high effective pitch.

Explanation

Question 102 of 171

1

Na rodzaj korkociągu główny wpływ mają następujące czynniki. The type of spin is mainly influenced by the following factors:

Select one of the following:

  • Położenie środka ciężkości samolotu; -rozłożenie mas na samolocie; - usytuowanie i wielkość usterzeń. The plecement of center of gravity of the airplane; -distribution of mass in The airplane; -location and size of the tailplane.

  • Położenie środka ciężkości samolotu; -rozłożenie mas na samolocie; - ustawienie klapki wyważającej. The plecement of center of gravity of the airplane; -distribution of mass in the airplane; -trim tabs settings.

  • Rozłożenie mas na samolocie; - ustawienie klapki wyważającej ; - usytuowanie i wielkość usterzeń. Distribution of mass in the airplane; - trim tabs settings ;-location and size of the tailplane

  • Ustawienie klapki wyważającej ; - położenie środka ciężkości samolotu; - usytuowanie i wielkość usterzeń. Trim tabs settings; -center of gravity of the airplane; -location and size of the tailplane.

Explanation

Question 103 of 171

1

The smallest rate of descent in glide flight is when the plane is flown with the following speed:

Select one of the following:

  • Economic.

  • Optimal.

  • Minimum.

  • Different depending on whether the plane is downwind or upwind.

Explanation

Question 104 of 171

1

The highest glide ratio in a glide is achieved when the plane is flown (in a calm air) with the following speed:

Select one of the following:

  • Optimal.

  • Minimum.

  • Mc Credy'ego.

  • Economic.

Explanation

Question 105 of 171

1

Power load is called:

Select one of the following:

  • The ratio of the engine power to the weight of the aircraft.

  • The ratio of the necessary power to the aircraft weight.

  • The ratio of the weight of the airplane engine power.

  • The ratio of the weight of the aircraft to the necessary power.

Explanation

Question 106 of 171

1

Objawem przejścia samolotu do lotu w fazie przeciągnięcia jest zazwyczaj: Symptom of an airplane in the transition phase is usually:

Select one of the following:

  • Występowanie drgań samolotu lub sterów; -samoczynne zwiększanie pochylenia. Among the symptoms of a stalled airplane are usually:

  • Występowanie drgań samolotu lub sterów; -samoczynne zwiększanie prędkości postępowej. Plane vibration or controls vibration; airspeed increase.

  • Zmniejszanie prędkości opadania; - samoczynne zwiększanie prędkości postępowej. Rate of descent reduction; airspeed increase.

  • Samoczynne zwiększanie pochylenia; -zmniejszanie prędkości opadania. Pitch-down movement; rate of descent reduction.

Explanation

Question 107 of 171

1

Interference drag is caused by:

Select one of the following:

  • An airflow distortion at places where aircraft components join together.

  • Interference of drag induced at the airfoil.

  • Formation of vortices at airfoil tips.

  • Wave interference in subsonic flows.

Explanation

Question 108 of 171

1

Pulling the yoke causes:

Select one of the following:

  • Increase in aircraft load factor "n".

  • Reduction in aircraft load factor "n".

  • Increase in the coefficient of drag, which causes a reduction in load factor "n".

  • Change in load factor "n" value from positive to negative.

Explanation

Question 109 of 171

1

During the stability analysis of plane it is necessary to take into account:

Select one of the following:

  • The balance of forces and moments acting on the plane.

  • The balance of forces acting on an airplane.

  • The balance of moments acting on the plane.

  • Only the mass distribution within the plane.

Explanation

Question 110 of 171

1

When you yaw the airplane, the powerplant giroscopic moment:

Select one of the following:

  • Causes pitch.

  • Causes additional yaw.

  • Does not cause a significant change.

  • Causes roll.

Explanation

Question 111 of 171

1

When you pitch the airplane, the powerplant giroskopic moment:

Select one of the following:

  • Causes yaw.

  • Causes roll.

  • Causes additional pitch.

  • Does not cause additional changes.

Explanation

Question 112 of 171

1

During the approach to landing on an airplane with a variable pitch:

Select one of the following:

  • After the reduction of manifold pressure the propeller shall be set to fine pitch.

  • After the reduction of manifold pressure the propeller shall be set to coarse pitch.

  • After setting the propeller to fine pitch the mainfold pressure shall be reduced.

  • After setting the propeller to fine pitch the mainfold pressure shall be increased.

Explanation

Question 113 of 171

1

When you perform an engine test before flight the advance ratio is:

Select one of the following:

  • Zero.

  • Greater than zero.

  • Less than zero.

  • Equal to Y.

Explanation

Question 114 of 171

1

When you roll the airplane, the powerplant giroscopic moment:

Select one of the following:

  • Does not cause any significant change.

  • Causes yaw.

  • Causes pitch.

  • Causes additional roll.

Explanation

Question 115 of 171

1

During steady level flight, the rotating propeller is trying to turn the plane in the direction opposite to the direction of rotation of the blade. That torque is called:

Select one of the following:

  • Momentem oporowym. Torque reaction.

  • Momentem giroskopowym. Giroscopic torque.

  • Momentem mimośrodowym. Eccentric torque.

  • Momentem napędowym. Driving torque.

Explanation

Question 116 of 171

1

During maneuvers the pilot operates in a feedback loop to respond to the received signals. What are those main signals?

Select one of the following:

  • Signals of the flight path location.

  • Vibration of controls.

  • Sound Impressions.

  • Load factors

Explanation

Question 117 of 171

1

Location of center of pressure on a symmetrical profile, with an increasing angle of attack:

Select one of the following:

  • Is constant.

  • Moves aft.

  • Moves forward.

  • Is not fixed and depends on the speed of flight.

Explanation

Question 118 of 171

1

Propeller slip is:

Select one of the following:

  • The difference between geometric and effective pitch.

  • The difference between effective and geometric pitch.

  • The difference between geometric pitch and advanced ratio.

  • The difference between effective speed and advanced ratio.

Explanation

Question 119 of 171

1

Dynamic stall differes from the static stall, because during the dynamic one:

Select one of the following:

  • There is a rapid change of wing angle of attack.

  • There is a slow change of wing angle of attack.

  • The airplane is dynamically stable.

  • The airplane is statically stable.

Explanation

Question 120 of 171

1

Stall is a state in which:

Select one of the following:

  • Flight takes place above critical angle of attack.

  • Flight takes place at a critical angle of attack.

  • Flight takes place at subcritical angle of attack.

  • The airplane does not respond to rudder deflection due to the low-speed.

Explanation

Question 121 of 171

1

Increase of the aircraft pitching moment "Delta M" resulting from the yoke movement is Delta M = Delta L * lH, where:

Select one of the following:

  • lH – odległość między środkiem ciężkości samolotu i środkiem aerodynamicznym usterzenia poziomego; Delta PZH – przyrost siły nośnej na usterzeniu wysokości. lH - the distance between the center of gravity of the airplane and the horizontal tailplane aerodynamic center; Delta L - increase of the lift force on the elevator.

  • lH - the distance between the wing aerodynamic center and and the horizontal tailplane aerodynamic center; Delta L - increase of the lift force on the elevator.

  • lH- the distance between the wing aerodynamic center and and the horizontal tailplane aerodynamic center; Delta L - increase of the aerodynamic force on the elevator.

  • lH – odległość między środkiem ciężkości samolotu i środkiem aerodynamicznym usterzenia poziomego; Delta PZH – przyrost siły aerodynamicznej na usterzeniu wysokości. lH- the distance between the center of gravity of the airplane and the horizontal tailplane aerodynamic center; Delta L - increase of the lift force on the elevator.

Explanation

Question 122 of 171

1

When considering the stability of the airplane in an Cartesian (XYZ) coordinate system, we assume that all three axes pass through:

Select one of the following:

  • Center of gravity of the airplane.

  • The aerodynamic center of aerofoil.

  • The aerodynamic center of the aircraft.

  • The neutral point of the plane.

Explanation

Question 123 of 171

1

The aircraft flies horizontally at economic speed. To establish horizontal fly with minimal speed (Vs) we should to do:

Select one of the following:

  • Reduce speed.

  • Push the aerodynamic center of the airfoil.

  • All answers are wrong.

  • Shift a neutral centre of plane balance.

Explanation

Question 124 of 171

1

An airplane during stall configuration is:

Select one of the following:

  • Unstable statically longitudinally and laterally.

  • Only unstable statically longitudinally.

  • Only unstable statically laterally.

  • Statically stable laterally and longitudinally.

Explanation

Question 125 of 171

1

The plane in the spin phase is characterized by:

Select one of the following:

  • Static longitudinal unstability.

  • Increased static longitudinal stability.

  • Reduced static longitudinal stability.

  • Neutral static longitudinal stability.

Explanation

Question 126 of 171

1

Aircrafts used in general aviation are usually constructed that:

Select one of the following:

  • After developed going into a spin, it will be the steep spin.

  • After developed going into a spin, it will be the flat spin.

  • It is unable developed into a spin.

  • Immediately, followed self-removal recover from a spin.

Explanation

Question 127 of 171

1

The geometric Pitch of the propeller is

Select one of the following:

  • The theoretical distance moved forward in each complete revolution of the propeller.

  • The theoretical distance moved forward in each complete revolution when blades are set on angle of attack (AoA) alpha<0 °.

  • The theoretical distance moved forward in each complete revolution when blades are set on angle of attack (AoA) alpha>0 °.

  • The theoretical distance moved forward in each complete revolution when blades are set on angle of attack (AoA) alpha = ß.

Explanation

Question 128 of 171

1

Actual pitch propeller:

Select one of the following:

  • The actual distance moved forward in each complete revolution of propeller.

  • The actual distance moved forward in each complete revolution of propeller when blades are set on angle of attack (AoA) alpha = 0 °

  • The actual distance moved forward in each complete revolution of propeller when blades are set on angle of attack (AoA) alpha = ß

  • The way which will take suitable choice point of the propeller during an one full revolution.

Explanation

Question 129 of 171

1

The propeller efficiency is equal zero only when:

Select one of the following:

  • Ciąg śmigła T=0 lub posuw śmigła =0. Thrust of propeller is T = 0 or the advance ratio of "J" is = 0 J=V/NxD where V=TAS in feet/sec, N=propeller rotation/sec, D=propeller diametr in inch.

  • Ciąg śmigła T=0 i posuw śmigła =0. Thrust of propeller is T = 0 and the advance ratio of "J" is = 0 J=V/NxD where V=TAS in feet/sec, N=propeller rotation/sec, D=propeller diametr in inch.

  • Ciąg śmigła T=0. Thrust of propeller is T = 0.

  • Posuw śmigła =0. The advance ratio of "J" J=V/NxD where V=TAS in feet/sec, N=propeller rotation/sec, D=propeller diametr in inch.

Explanation

Question 130 of 171

1

The state of balance, when the mass is usually existing and to which always returns after being displaced from a given equilibrium position is named:

Select one of the following:

  • Static stability.

  • Statically unstable.

  • Statically neutral.

  • Dynamic stability.

Explanation

Question 131 of 171

1

Dynamic lateral stability mainly depends from:

Select one of the following:

  • The dihedral - the fin and rudder areas - the distance between tailplane centre of pressure (CP) and centre of gravity (CG).

  • The dihedral - the fin and rudder areas - the tailplane areas.

  • The fin and rudder areas - the tailplane areas - the distance between tailplane centre of pressure (CP) and centre of gravity (CG).

  • The distance between tailplane centre of pressure (CP) and centre of gravity (CG) - the dihedral.

Explanation

Question 132 of 171

1

Dynamic longitudinal stability mainly depends from:

Select one of the following:

  • The layout of plane masses - the fin and the rudder areas - the distance between tailplane centre of gravity (CG) and centre of gravity (CG).

  • The layout of plane masses - the size of stabilizer - the size of fin and rudder.

  • The area of stabilizer - the size of fin and stabilizer- the distance between tailplane centre of pressure (CP) and centre of gravity (CG).

  • The area of fin and rudder - the distance between tailplane centre of pressure (CP) and centre of gravity and the layout of plane masses.

Explanation

Question 133 of 171

1

Dynamic stability is:

Select one of the following:

  • The ability to self-balance return of the aircraft to given equilibrium position after cessation of interference.

  • The ability to maintain balance and prevent of its change.

  • The ability to change the steady-state flight under an affect of the suitable action of the control.

  • The ability to maintain control of the aircraft which is operate under external dynamic loads.

Explanation

Question 134 of 171

1

Static directional stability depends from:

Select one of the following:

  • The fin and rudder area - the distance of the empennage from the center of gravity.

  • The the fin and rudder area - the wing area.

  • The tailplane position from the centre of gravity (CG) - the load of the aircraft.

  • The wing surface - the load of the aircraft.

Explanation

Question 135 of 171

1

Static longitudinal stability mainly depends from:

Select one of the following:

  • Position of the centre of gravity (CG) of the airplane - the tailplane area and the tailplane position from the centre of gravity (CG).

  • Position of the centre of gravity (CG) of the airplane - the tailplane area and of the fin and rudder area.

  • The tailplane area - the fin and rudder area - the tailplane position from the centre of gravity (CG).

  • The fin and rudder area - the tailplane position from the centre of gravity (CG) - the position of the centre of gravity (CG) of the airplane.

Explanation

Question 136 of 171

1

Static lateral stability mainly depends from:

Select one of the following:

  • The dihedral, the area of the fin and rudder, the high wing or low-wing position.

  • The dihedral, the area of the fin and rudder, the position of centre gravity (CG) of the airplane.

  • The area of the fin and rudder, the position of centre gravity (CG) of the airplane- or a the high wing or lowwing position.

  • The centre of gravity (CG) of the airplane, the high wing or low-wing position and the dihedral.

Explanation

Question 137 of 171

1

Static stability is:

Select one of the following:

  • The initial tendency that an aircraft displays after being displaced from a given equilibrium position.

  • The ability to change the a given equilibrium position by the influence of suitable flying control surface.

  • Ability to maintain an aircraft control inflenced by external dynamic forces.

  • The ability to self-balance equilibrium position return of the aricraft, when interference will stop.

Explanation

Question 138 of 171

1

A controllability is:

Select one of the following:

  • The ability to alter of the fixed flight by using of the flying control surfaces.

  • The ability to perform large movements with use of the control column and ruddler.

  • The ability to self-balance return to equilibrium when will stop operate interferences.

  • The ability to maintain balance and prevent of its change.

Explanation

Question 139 of 171

1

The ratio of work done by the propeller to the power consumed by a propeller from the engine is called:

Select one of the following:

  • The propeller efficiency.

  • The propeller-feed.

  • The slipslipping Propeller.

  • The propeller pitch.

Explanation

Question 140 of 171

1

Stosunek prędkości lotu "V" do prędkości obwodowej danego przekroju śmigła "u" nazywamy: The quatient of airspeed TAS to Revolution per Minute (RPM) of the propeller blade cross-section is called:

Select one of the following:

  • Posuwem. The advance ratio of "J" J=V/NxD where V=TAS in feet/sec, N=propeller rotation/sec, D=propeller diametr in inch.

  • Poślizgiem geometrycznym. The geometric pitch.

  • Poślizgiem aerodynamicznym. The effective pitch.

  • Skokiem śmigła. The teoretical distance moved.

Explanation

Question 141 of 171

1

Propeller of aircraft, in order to maximize of efficiency should to be:

Select one of the following:

  • Twisted geometrically so that the angle of attack of consecutive blade cross-sections during of the flight was similar.

  • Twisted geometrically so that the angle of attack of consecutive blade crosssections increase with distance from the axis of the propeller rotation.

  • Twisted geometrically so that the angle of attack of consecutive blade crosssections decrease as the distance from the axis of the propeller rotation.

  • Twisted geometrically so that the angle of attack of consecutive blade crosssections is similar to the critical angle of attack (AoA).

Explanation

Question 142 of 171

1

In order to recovery of the plane from autorotation (spin) it is necesary:

Select one of the following:

  • Push down the full stick, apply full opposite rudder into the direction of rotation.

  • Apply full opposite rudder into the rotation of the spin, pull up the stick.

  • Apply roll ailerons into the opposite direction of roll, pull up the stick.

  • Apply roll ailerons into the opposite direction of roll, push down the stick.

Explanation

Question 143 of 171

1

W celu wyprowadzenia samolotu z fazy przeciągnięcia do lotu ustalonego należy: Apply roll ailerons into the opposite direction of roll, push down the stick.

Select one of the following:

  • Zwiększyć siłę nośną na skrzydle poprzez oddanie drążka sterowego.Increase the lift on the wing by push down of the stick or control column.

  • Zwiększyć siłę nośną na skrzydle poprzez pociągnięcie drążka sterowego. Increase the lift on the wing by pull up of the stick or control column.

  • Zmniejszyć siłę nośną na skrzydle poprzez pociągnięcie drążka sterowego. Reduce the lift on the wing by pull up of the stick or control column.

  • Zmniejszyć siłę nośną na skrzydle poprzez oddanie drążka sterowego. Reduce the lift on the wing by push down of the stick or control column.

Explanation

Question 144 of 171

1

In order to recovery of the plane from the spin in following sequence:

Select one of the following:

  • Push down the full stick, apply full opposite rudder into the rotation of the spin, after the terminate of rotation set rudder in neutral possition and recover from the dive.

  • Apply full opposite rudder into the rotation of the spin, pull up the stick,after the terminate of rotation set rudder in neutral possition and recover from the dive.

  • Apply roll ailerons into the opposite direction of roll, pull up the stick, after the terminate of rotation set rudder in neutral possition and recover from the dive.

  • Apply roll ailerons into the opposite direction of roll, push down the stick, after the terminate of rotation set rudder in neutral possition and recover from the dive.

Explanation

Question 145 of 171

1

W celu zmniejszenia pochylenia samolotu: In order to reduce the inclination of the plane:

Select one of the following:

  • Należy wychylić drążek sterowy na siebie. The stick shall to be pulled.

  • Należy wychylić ster wysokości w dół. The elevator or stabilator should to be pushed downward.

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „w górę” . The vector of incease of the lift on the elevator or stabilator must to have into up direction.

  • Przyrost momentu pochylającego samolot musi mieć wartość dodatnią. The increase of the pitching moment of the aircraft must to have a positive value.

Explanation

Question 146 of 171

1

W celu zmniejszenia pochylenia samolotu: In order to reduce the inclination of the plane:

Select one of the following:

  • Przyrost momentu pochylającego samolot musi mieć wartość do ujemną. The increase of the pitching moment of the aircraft must to have a negative value.

  • Należy wychylić ster wysokości w dół. The elevator or stabilator should to be pushed downward.

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „w górę”. The vector of incease of the lift on the elevator or stabilator must to have into up direction.

  • Należy wychylić drążek sterowy od siebie. The stick shall to be pushed.

Explanation

Question 147 of 171

1

W celu zmniejszenia pochylenia samolotu: In order to reduce the inclination of the plane:

Select one of the following:

  • Należy wychylić ster wysokości w górę.The elevator or stabilator should to be pushed upward.

  • Przyrost momentu pochylającego samolot musi mieć wartość dodatnią. The increase of the pitching moment of the aircraft must to have a positive value.

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „w górę” . The vector of incease of the lift on the elevator or stabilator must to have into up direction.

  • Należy wychylić drążek sterowy od siebie. The stick shall to be pushed.

Explanation

Question 148 of 171

1

W celu zmniejszenia pochylenia samolotu: In order to reduce the inclination of the plane:

Select one of the following:

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „w dół” . The vector of incease of the lift on the elevator or stabilator must to have into down direction.

  • Należy wychylić ster wysokości w dół. The elevator or stabilator should to be pushed downward.

  • Przyrost momentu pochylającego samolot musi mieć wartość dodatnią. The increase of the pitching moment of the aircraft must to have a positive value.

  • Należy wychylić drążek sterowy od siebie.The stick shall to be pushed.

Explanation

Question 149 of 171

1

W celu zwiększenia pochylenia samolotu: In order to increase the inclination of the plane:

Select one of the following:

  • Należy wychylić drążek sterowy od siebie. The stick shall to be pulled.

  • Przyrost momentu pochylającego samolot musi mieć wartość do ujemną. The increase of the pitching moment of the aircraft must to have a negative value.

  • Należy wychylić ster wysokości do góry. The elevator or stabilator should to be pushed downward.

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „w dół”. The vector of incease of the lift on the elevator or stabilator must to have into down direction.

Explanation

Question 150 of 171

1

W celu zwiększenia pochylenia samolotu: In order to increase the inclination of the plane:

Select one of the following:

  • Należy wychylić ster wysokości w dół. The elevator or stabilator should to be pushed downward.

  • Należy wychylić drążek sterowy na siebie. The stick shall to be pulled.

  • Przyrost momentu pochylającego samolot musi mieć wartość do ujemną. The increase of the pitching moment of the aircraft must to have a negative value.

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „w dół”.The vector of incease of the lift on the elevator or stabilator must to have into down direction.

Explanation

Question 151 of 171

1

W celu zwiększenia pochylenia samolotu: In order to increase the inclination of the plane:

Select one of the following:

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „w górę”. The vector of incease of the lift on the elevator or stabilator must to have into up direction.

  • Należy wychylić drążek sterowy na siebie. The elevator shoud to be upward.

  • Należy wychylić ster wysokości do góry. The stick shall to be pulled.

  • Przyrost momentu pochylającego samolot musi mieć wartość do ujemną. Increasing of the aircraft nose-down pitch moment must be positive.

Explanation

Question 152 of 171

1

W celu zwiększenia pochylenia samolotu: To increase up the pitch of the plane we should to do:

Select one of the following:

  • Wszystkie odpowiedzi są poprawne. All responses are correct.

  • Przyrost momentu pochylającego samolot musi mieć wartość dodatnią. Increasing of the aircraft nose-up pitch moment must to be positive.

  • Wektor przyrostu siły nośnej na usterzeniu poziomym musi mieć zwrot „do góry”. Increase of the lift force vector on the horizontal tail assembly.

  • Należy wychylić drążek sterowy na siebie. The stick shall to be pulled.

Explanation

Question 153 of 171

1

In which document are there information about the performance of the aircraft (helicopter, aircraft, etc.)?

Select one of the following:

  • In an Aeroplane Flight Manual(AFM) or a Pilot Operational Handbook (POH)

  • In the Technical Manual.

  • In the service bulletins of Civil Aircraft Inspectorate Board.

  • The Civil Aviation Authority regulations.

Explanation

Question 154 of 171

1

In case when the propeller angle of attack(AoA) is equals the blade angle of the propeller it is true that:

Select one of the following:

  • The slip of propeller is = 0 also the effective and geometric pitch are the equal.

  • The slip of propeller is = 0 and propeller effective and geometric pitch are = 0.

  • The slip of propeller is = 0 and the propeller slip is negative.

  • The Airspeed of plane is nu = 0 and the propeller slip is = 0.

Explanation

Question 155 of 171

1

In an quiet air, the glide-angle with off an engine during incease of aicraft load:

Select one of the following:

  • Remains unchanged.

  • Increases.

  • Decreases.

  • Is changes and can be read by drawing the speed polar of plane.

Explanation

Question 156 of 171

1

In a fixed straight horizontal flight the load factor of plane is:

Select one of the following:

  • n=1

  • n=0

  • 0 <n> 1

  • n>1

Explanation

Question 157 of 171

1

In the fixed turn of plane the load factor "n" is:

Select one of the following:

  • n>1

  • n=1

  • n=0

  • 0<n<1

Explanation

Question 158 of 171

1

W wyniku niewielkiego zwiększania kąta natarcia alpha=alpha optymalne: As a achieving result of the glide-angle:

Select one of the following:

  • Procentowe zwiększenie Cx będzie większe od procentowego zwiększenia Cz. The L/D ratio will achieve the maximum of value.

  • Procentowe zwiększenie Cz’+F2396 będzie większe od procentowego zwiększenia Cx. The proportional increase of CL will not increse from of the proportional increase of Cd.

  • Procentowe zwiększenie Cx będzie takie same jak procentowe zwiększenia Cz. The proportional increase in Cx will be the same as the proportional increase in Sun.

  • Doskonałość profilu nieznacznie wzrośnie. The proportional increse of Cx will be greather then the proportional increse od Cl.

Explanation

Question 159 of 171

1

W wyniku niewielkiego zwiększania kąta natarcia &alpha;=&alpha; optymalne : As a result of a slight increase of the angle of attack (AoA) over glide-angle:

Select one of the following:

  • Stosunek Cz/Cx zmaleje. The L/D ratio of airfoil will increase.

  • Stosunek Cz/Cx wzrośnie. The ratio of D/L will increase.

  • Stosunek Cz/Cx nie zmieni się. The ratio of L/D will will not change.

  • Doskonałość profilu nieznacznie wzrośnie. The ratio of L/D will will decrease.

Explanation

Question 160 of 171

1

W wyniku niewielkiego zwiększania kąta natarcia &alpha;=&alpha; optymalne : As a result of a slightly increase the angle of attack (AoA) over glide-angle:

Select one of the following:

  • Doskonałość profilu zmaleje . The L/D ratio of airfoil will increase.

  • Doskonałość profilu wzrośnie. The L/D ratio of airfoil will decrease.

  • Doskonałość profilu nie zmieni się. The L/D ratio of airfoil will not change.

  • Stosunek Cz/Cx wzrośnie. The D/L ratio of airfoil will increase.

Explanation

Question 161 of 171

1

Aileron deflection to the left during the stall will cause:

Select one of the following:

  • Roll of the plane to the right and start autorotation.

  • Roll of the plane to the left.

  • Roll of the plane to the right till the return of the stick into the neutral position.

  • Roll of the plane to the left till to the return of the stick into the neutral position.

Explanation

Question 162 of 171

1

Flap deflection is usually accompanied by:

Select one of the following:

  • Increase of the Cz, increase of the Cx and decrease of the L/D ratio.

  • Increase of the Cz, increase of the Cx and increase of the L/D ratio.

  • Increase of the Cz, increase of the Cx not changed of the L/D ratio.

  • Displacement of the neutral balance center of the plane.

Explanation

Question 163 of 171

1

Wykres zależności Cz = f(Cx) wykonany na podstawie pomiarów w czasie lotu nazywamy: A graph the allegiance of the CD as a function of the CL Cl = f (Cx) performed on the basis of measurements during a flight, is called:

Select one of the following:

  • Biegunową samolotu.The Drag Polar of the aircraft.

  • Biegunową prędkości samolotu. The speed polar of the aircraft.

  • Biegunową profilu. The wing polar.

  • Biegunową skrzydła. The airfoil polar.

Explanation

Question 164 of 171

1

Which property is related to a decrease of airflow in the boundary layer of airofoil?

Select one of the following:

  • The viscous of the air.

  • The air density.

  • The stagnacy of the air

  • The air ballance.

Explanation

Question 165 of 171

1

Zaleca się, aby zmiana mocy z przelotowej na nominalną (śmigło o przestawianym skoku) odbywała się w następujący sposób: It is recommended that the change of cruising power to nominal (controllable pitch propeller (CPP) or variable pitch propeller) is made as follows:

Select one of the following:

  • Zmniejszenie skoku śmigła, a później zwiększenie ciśnienia ładowania. First increasing of a propeller pitch and then increase of the throttle.

  • Zmniejszenie ciśnienia ładowania, a później zwiększenie skoku śmigła. First reducing of the throttle then increasing of the propeller pitch.

  • Zwiększenie skoku śmigła, a później zmniejszenie ciśnienia ładowania. Increasing of the propeller pitch, and then reducing of the throttle.

  • Zwiększenie ciśnienia ładowania, a później zmniejszenie skoku śmigła skoku śmigła. Increasing throttle and then decrease of the propeller pitch.

Explanation

Question 166 of 171

1

It is recommended that the change of take off power to nominal (controllable pitch propeller (CPP) or variable pitch propeller) is made as follows:

Select one of the following:

  • First reducing of the throttle next increasing the propeller pitch.

  • First increasing the propeller pitch next reducing the throttle.

  • Increase throttle next decrease the propeller pitch.

  • Reducing of propeller pitch next increase the throttle.

Explanation

Question 167 of 171

1

Zapas stateczności statycznej podłużnej samolotu to: An aircraft static margin of a static longitudinal stability this is:

Select one of the following:

  • Odległość pomiędzy środkiem ciężkości samolotu i środkiem równowagi obojętnej. The distance between the Center of Gravity of the aircraft and the Neutral Point.

  • Odległość pomiędzy środkiem ciężkości samolotu i środkiem aerodynamicznym The distance between the Center of Gravity of the airplane and aerodynamic center (AC).

  • Odległość pomiędzy środkiem równowagi obojętnej i środkiem aerodynamicznym płata. The distance between the Neutral balance center and the aerodynamic center (AC).

  • Odległość pomiędzy środkiem aerodynamicznym usterzenia i środkiem aerodynamicznym płata.
    The distance between the aerodynamic center of control surface and the aerodynamice center of the wing.

Explanation

Question 168 of 171

1

The ability to self-acting return of airplane into equilibrium position after cessation of disturbance is called:

Select one of the following:

  • The Dynamic Stability.

  • The static stability.

  • The Static Controllability.

  • The Dynamic controllability.

Explanation

Question 169 of 171

1

Zwichrzenie aerodynamiczne płata charakteryzuje się tym, że: An aerodynamic twist angle of a wing is characterized by:

Select one of the following:

  • Na końcówkach płata stosuje się profile, na których oderwanie strug dla alpha;kryt jest mniej intensywne. On the tips od the wings there are airfoils, where the separated airflow leaving the wing for Absolute Angle of Attack (Absolute AoA) is less intense.

  • Cięciwy profilów geometrycznych w kolejnych przekrojach nie leżą w jednej płaszczyźnie. Tips of wings are twistet down when speed is equal to 0.

  • Końcówki płata wygięte są w dół, jeżeli prędkość napływu strug =0. Tips of wings are twistet down when speed is equal to 0.

  • Końcówki płata wygięte są w górę podczas lotu. Tips of wings are curved up during in flight.

Explanation

Question 170 of 171

1

Zwichrzenie geometryczne płata charakteryzuje się tym, że: A geometric twist of a wing is characterized by:

Select one of the following:

  • Cięciwy profili geometrycznych w kolejnych przekrojach nie leżą w jednej płaszczyźnie. Geometric chord profiles in subsequent sections do not lie in one plane.

  • Końcówki płata wygięte są w dół, jeżeli prędkość napływu strug =0. Tips of wings are twistet down when speed is equal to 0.

  • Końcówki płata wygięte są w górę podczas lotu. Tips of wings are curved up during in flight.

  • Na końcówkach płata stosuje się profile, na których oderwanie strug dla alpha;kryt jest mniej intensywne. On the tips od the wings there are airfoils, where the separated airflow leaving the wing for Absolute Angle of Attack (Absolute AoA) is less intense.

Explanation

Question 171 of 171

1

Zwiększenie obciążenia jednostkowego powierzchni powoduje: Increasing the unit loading of the planform area causes:

Select one of the following:

  • Wydłużenie długości staru i lądowania - wzrost prędkości minimalnej - spadek maksymalnej prędkości wznoszenia. Take off and landing distance extending- increase of minimal speed (Vs)- decrease in maximal climbing rate(RoCmax).

  • Skrócenie długości startu i lądowania - wzrost prędkości minimalnej - spadek maksymalnej prędkości. Reducing of Take off and landing distance - increse in minimal speed(Vs) - decrease in maximal climbing rate(RoCmax).

  • Wydłużenie długości startu i lądowania - spadek prędkości minimalnej - spadek maksymalnej prędkości wznoszenia. Take off and landing distance extending - decrease of minimal speed(Vs) - decrease in maximal climbing rate(RoCmax).

  • Wydłużenie długości staru i lądowania - wzrost prędkości minimalnej - wzrost maksymalnej prędkości wznoszenia. Take off and landing distance extending - increase in minimal speed(Vs) - increase in maximal climbing rate(RoCmax).

Explanation

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