Roman Eidia
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Quiz on Principles Of Flight, created by Roman Eidia on 30/09/2018.

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Roman Eidia
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Principles Of Flight

Frage 1 von 200

1

Are cambered aerofoils much more "sensitive" to contamination than laminar profiles?

Wähle eine der folgenden:

  • No.

  • Yes.

  • No, but only for small angles of attack.

  • Yes, but only at high angles of attack.

Erklärung

Frage 2 von 200

1

To prevent airleron flutter it is necessary to:

Wähle eine der folgenden:

  • Increase the bending rigidity of the wing and apply mass balance to the aileron.

  • Apply aerodynamic balance - move the wing CoG closest to the axis of torsion.

  • Apply balance tab and increase the torsional rigidity of the wing.

  • Apply anti-balance tab and aileron mass balance.

Erklärung

Frage 3 von 200

1

To prevent bending-torsional flutter it is necessary to:

Wähle eine der folgenden:

  • Increase the torsional rigidity of the wing and move the wing CoG closest to the axis of torsion.

  • Apply aerodynamic balance - move the wing CoG closest to the axis of torsion.

  • Apply balance tab and increase the torsional rigidity of the wing.

  • Apply anti-balance tab and aileron mass balance.

Erklärung

Frage 4 von 200

1

To prevent airleron reversal it is necessary to:

Wähle eine der folgenden:

  • Increase the torsional rigidity of the wing.

  • Apply aerodynamic ballance.

  • Apply balance tab.

  • Apply anti-balance tab.

Erklärung

Frage 5 von 200

1

To prevent buffeting it is necessary to:

Wähle eine der folgenden:

  • Use the T-tail configuration and carefully design wing-fuselage joint.

  • Use the T-tail configuration and trim tab.

  • Use trim tab and carefully design wing-fuselage joint.

  • Increase the bending and torsional rigidity of the tailplane.

Erklärung

Frage 6 von 200

1

An aerodynamic leading edge is a line joining the points of airfoil where:

Wähle eine der folgenden:

  • Airflow velocity is zero and the pressure equals stagnation pressure.

  • Airflow velocity is zero.

  • The pressure is greater than the stagnation pressure.

  • Airflow velocity is zero and the pressure is at its minimum value.

Erklärung

Frage 7 von 200

1

Lack of airlerons mass balance during high-speed flight is a direct cause of:

Wähle eine der folgenden:

  • Aileron flutter.

  • Bending- torsional flutter.

  • Airleron reversal.

  • Wing torsional divergence.

Erklärung

Frage 8 von 200

1

Buffeting means:

Wähle eine der folgenden:

  • Shaking of control surfaces.

  • Bending- torsional vibrations.

  • Aileron flatter.

  • Tailplane flatter.

Erklärung

Frage 9 von 200

1

An object moves with the speed V on a circular track. A double increase of the object's speed will cause the following:

Wähle eine der folgenden:

  • Angular speed "Omega" doubles - centripetal accelaration "ar" increases four times.

  • Angular speed "Omega" doubles - centripetal accelaration "ar" doubles.

  • Angular speed "Omega" increases four times - centripetal accelaration "ar" increases four times.

  • Angular speed "Omega" increases four times - centripetal accelaration "ar" doubles.

Erklärung

Frage 10 von 200

1

An object moves with the speed V on a circular track. A double increase of the track's radius will cause the following:

Wähle eine der folgenden:

  • Angular speed "Omega" decreases by half - the object's full period path doubles - centripetal accelaration "ar" decreases by half.

  • Angular speed "Omega" decreases by half - the object's full period path decreases by half - centripetal accelaration "ar" decreases by half.

  • Angular speed "Omega" decreases by half - the object's full period path doubles - centripetal accelaration "ar" doubles.

  • Angular speed "Omega" decreases by half - the object's full period path double - centripetal accelaration "ar" stays constant.

Erklärung

Frage 11 von 200

1

An object moves with the speed "V" on a circular track with radius "R". The resultant acceleration vector is always directed:

Wähle eine der folgenden:

  • Towards the track center.

  • Towards the outside of the track.

  • Since the speed "V" is constant, no acceleration acts on the body.

  • Tangent to the circle.

Erklärung

Frage 12 von 200

1

Static pressure at the separation point (change from laminar flow to turbulent flow) is:

Wähle eine der folgenden:

  • Minimal on the upper surface and maximal on the bottom surface.

  • Maximal on the upper surface and mnimal at the bottom surface.

  • Minimal on the upper surface ana minimal on the bottom surface.

  • Maximal on the upper surface and maximal on the bottom surface.

Erklärung

Frage 13 von 200

1

What does "the universal gas law" mean?

Wähle eine der folgenden:

  • Relation between static pressure, density, temperature and gas constant p=rho*g*R*T [Pa].

  • Relation between the air pressure and its temperature

  • Equation of a balance between the air pressure and its humidity.

  • Equation of the balance between the air pressure and earth acceleration

Erklärung

Frage 14 von 200

1

What dose the term " controllability " of a flying object ( plane, helicopter, glider, hang-glider etc) mean?

Wähle eine der folgenden:

  • Ability of the object to "respond" to control impulses induced by the pilot.

  • Assurance that acrobatic exercises are permitted.

  • Assurance that the object's performance is as designed.

  • Assurance that the object is statically and dynamically stable.

Erklärung

Frage 15 von 200

1

What does "stagnation pressure" mean?

Wähle eine der folgenden:

  • The difference between the dynamic and static pressure.

  • The highest measured pressure.

  • The lowest measured pressure.

  • The sum of a dynamic and static pressure.

Erklärung

Frage 16 von 200

1

What is a "laminar flow"?

Wähle eine der folgenden:

  • Undisturbed flow from the leading edge to the separation point.

  • Undisturbed flow along the entire chord, with air streams adhering to the profile.

  • Disturbed (turbulent) flow along the entire profile chord.

  • Disturbed (turbulent) flow along the entire profile chord, with maintained stream adherence to the profile.

Erklärung

Frage 17 von 200

1

What does the aircraft (helicopter, glider, etc.) "absolute ceiling" mean?

Wähle eine der folgenden:

  • The highest theoretical altitude that the aircraft is able to climb.

  • An altitude calculated in the design project of an aircraft.

  • The altitude at which the aircraft still maintains the climbing ability of 0,5m/s.

  • The altitude of the atmospere surrounding the Earth.

Erklärung

Frage 18 von 200

1

What does "static stability" of an object mean? (aircraft, helicopter, grinder, hang-grinder etc.)

Wähle eine der folgenden:

  • A tendency (in a form of force or a moment) to return to the former equilibrium after a disturbance.

  • Balance condition.

  • No reaction to balance disturbance.

  • Object static fluctuations around the lateral axis.

Erklärung

Frage 19 von 200

1

What does "airfoil Center of Pressure" mean?

Wähle eine der folgenden:

  • An imaginable point on the chord of an aerofoil at with the resultant force (of all aerodynamic forces) act.

  • A drag force application point.

  • A point at which the pressure value is average.

  • A center of the profile chord line.

Erklärung

Frage 20 von 200

1

What does the boundary layer mean"

Wähle eine der folgenden:

  • A layer of air flowing around an arbitrary aircraft element in which the stream velocity changes from zero to free stream velocity.

  • A turbulent air region in the area of fuslage and other aircraft elements joints.

  • A part of an airstream flowing a part of aircraft with A-type flow.

  • A part of an airstream which changes from laminar to A-type flow.

Erklärung

Frage 21 von 200

1

What is an "Aspect Ratio" of an aircraft or glider wing (or a propeller blade)?

Wähle eine der folgenden:

  • The ratio of wingspan to average chord length.

  • The ratio of wing or blade length to the chord length at the base of it.

  • The ratio of wingspan (rotor diameter) to the aircraft (helicopter) length.

  • The ratio of mean aerodynamic chord to the wing or blade length.

Erklärung

Frage 22 von 200

1

What is the elevation of the airport?

Wähle eine der folgenden:

  • The physical elevation (altitude) of an airport apron above mean sea level according to ISA.

  • The facade of an airport building.

  • The surface of the runway.

  • The slope of the main runway surface.

Erklärung

Frage 23 von 200

1

What is the air density?

Wähle eine der folgenden:

  • An air mass contained in a volume of 1m3.

  • The opposite of the atmospheric viscosity.

  • The number of molecules of oxygen and nitrogen in a 1cm3 volume.

  • The weight of 1 m3 air.

Erklärung

Frage 24 von 200

1

What is this the International Standard Atmosphere (ISA)?

Wähle eine der folgenden:

  • A set of values considered as standard of static pressure (p), temperatures (t/T) and the air density (rho) at different heights.

  • A set of intormation about atmospheric parameters held at the UN headquarters in New York.

  • A set of intormation about atmospheric parameters held at the ICAO headquarters in Montreal.

  • A collection of air chemical composition at different heights.

Erklärung

Frage 25 von 200

1

What is it a pressure altitude above the airport level?

Wähle eine der folgenden:

  • A reading of a pressure altimeter which is set to an airport pressure QFE.

  • A reading of a pressure altimeter which is set to sea level pressure QNH.

  • A reading of a radio altimeter.

  • The airport elevation.

Erklärung

Frage 26 von 200

1

What is pressure altitude above sea level?

Wähle eine der folgenden:

  • A reading of a pressure altimeter when it is set to the current sea level pressure QNH.

  • The airport elevation.

  • A reading of a pressure altimeter when it is set to the current airport pressure QFE.

  • A reading of a radio altimeter.

Erklärung

Frage 27 von 200

1

What is density altitude?

Wähle eine der folgenden:

  • Theoretical height, where the air density is equal to the standard density according to ISA.

  • The height according to international standard atmosphere (ISA).

  • The airport elevation height corrected for the current air density.

  • The pressure altitude corrected for humidity.

Erklärung

Frage 28 von 200

1

What is the standard height?

Wähle eine der folgenden:

  • A reading of a pressure altimeter when it is set to the standard value at sea level (QNH) this is 1013.25 hPa or 760 mm Hg.

  • A reading of a standard radio altimeter.

  • The airport elevation.

  • Density altitude, corrected for ambient temperature.

Erklärung

Frage 29 von 200

1

Is there any connection between air static pressure (p), the absolute temperature (T) and density (rho)?

Wähle eine der folgenden:

  • Yes, expressed as the Universal Gas Law p=rho*g*R*T [Pa], where g is the gravity constant g = 9.81 m/s2 and gas constant R = 29.2746 m/K.

  • Yes, expressed in Mallets Law p=R*g*rho*dT [Pa], where g is the gravity constant g = 9.81 m/s2 and air gas constant R = 29.2746 m/K.

  • Yes, expressed as a Crakow's form f [A, g, p, rho, T].

  • There is no connection.

Erklärung

Frage 30 von 200

1

Does the object (aircraft, helicopter, glider, hang-glider, etc.) statically unstable can be dynamically stable?

Wähle eine der folgenden:

  • No.

  • Yes.

  • Static stability is not important for the dynamic stability.

  • Fixed-wing aircraft - yes, Rotorcraft - no.

Erklärung

Frage 31 von 200

1

Does increase of stability affect controlability?

Wähle eine der folgenden:

  • Yes, controlability decreases.

  • Yes, controlability increses.

  • No, changes of stability do not affect controlability.

  • Yes, at large angles of attack the controlability increases and at small decreases.

Erklärung

Frage 32 von 200

1

What is the difference between static stability and dynamic stability of an object (airplane, helicopter, glider, hang-glider etc.)?

Wähle eine der folgenden:

  • The static stability takes into account only tendency to return to the equilibrium state, the dynamic stability takes into account objects's movement type.

  • There is no difference, the phenomenon is the same, just different names.

  • They differ in the importance - dynamic stability is more important.

  • The static stability concerns only balance on the ground, the dynamic stability - in-flight balance.

Erklärung

Frage 33 von 200

1

What is the "static instability" of an object (airplane, helicopter, glider, hang-glider etc.)?

Wähle eine der folgenden:

  • A tendency (in a form of force or a moment) to continue moving in the direction of displacement following a disturbance.

  • Lack of any object reaction following a disturbance.

  • Static fluctuations around the object lateral axis.

  • Trim balance condition.

Erklärung

Frage 34 von 200

1

What is the "neutral static stability" of an object (airplane, helicopter, glider, hang-glider etc.)?

Wähle eine der folgenden:

  • Lack of any object reacton following a disturbance.

  • A tendency (in a form of force or a moment) to return to equilibrium state following a disturbance.

  • Static fluctuations around the object lateral axis.

  • Trim balance condition.

Erklärung

Frage 35 von 200

1

What kind of profile doesn't create induced drag at zero angle of attack?

Wähle eine der folgenden:

  • Double convex symmetrical.

  • Plano-convex.

  • Concave-convex.

  • Double convex asymmetrical.

Erklärung

Frage 36 von 200

1

For a constant accelerated motion, double increase of time at a constant acceleration causes:

Wähle eine der folgenden:

  • A fourfold increase of the distance.

  • A double increase of the distance.

  • A double reduction of the distance.

  • A fourfold reduction of the distance.

Erklärung

Frage 37 von 200

1

For a constant accelerated motion, double increase of acceleration within a constant time causes:

Wähle eine der folgenden:

  • A double increase in the distance.

  • A fourfold increase in the distance.

  • A double reduction in the distance.

  • A fourfold reduction in the distance.

Erklärung

Frage 38 von 200

1

For a rectangular planform wing it is true that:

Wähle eine der folgenden:

  • The chord does not change along the wingspan.

  • The chord decreases along the wingspan.

  • The chord increases along the wingspan.

  • The chord at first increases and then decreases along the wingspan.

Erklärung

Frage 39 von 200

1

For the three wings with the same surface and the same wingspan, but with different planform (rectangular, tapered and elliptical), the Aspect Ratio is:

Wähle eine der folgenden:

  • The same for all planforms.

  • Highest for an elliptical planform and the smallest for a rectangular.

  • Highest for the rectangular planform and the smallest for an elliptical.

  • Highest for an elliptical planform and the smallest for the tapered.

Erklärung

Frage 40 von 200

1

For an established descent the following equation is true:

Wähle eine der folgenden:

  • Px=Q

  • Pz=Q

  • Q=Q

  • Pz=Px

Erklärung

Frage 41 von 200

1

What is the "drag polar"?

Wähle eine der folgenden:

  • A polar curve depicting the value of lift coefficient vs. drag coefficient.

  • A polar autorotation curve.

  • A chart of the power required.

  • A graph called "Titus Huber curve" in Poland.

Erklärung

Frage 42 von 200

1

The wing surface increasing devices are:

Wähle eine der folgenden:

  • Fowler flap and the leading edge flaps.

  • Winglets and trailing edge flaps.

  • Slots and the split flaps.

  • Trainling edge flaps and the split flaps.

Erklärung

Frage 43 von 200

1

Devices that move the separation point aft on an airfoil upper surface are called:

Wähle eine der folgenden:

  • Slats.

  • Trailing edge flaps.

  • Split flaps.

  • Fowler flap.

Erklärung

Frage 44 von 200

1

Devices that increace the camber of an airfoil are called:

Wähle eine der folgenden:

  • Leading edge flaps.

  • Winglets.

  • Slots.

  • All answers are correct.

Erklärung

Frage 45 von 200

1

The backward sweep of a wing causes:

Wähle eine der folgenden:

  • Increase in the lateral static stability

  • Reduction of the lateral static stability.

  • Reduction of the lateral static stability at positive angles of attack and the increase at negative.

  • Increase in the lateral static stability at positive angles of attack, and reduction at negative.

Erklärung

Frage 46 von 200

1

Aaerofoil glide ratio:

Wähle eine der folgenden:

  • Depends on the angle of attack.

  • Is a constant characteristic for the profile and corresponds to the (CL/CD)max.

  • Always increases when increasing angle of attack.

  • Always increases when decreasing angle of attack.

Erklärung

Frage 47 von 200

1

Doubling an airflow velocity in a closed tunnel will result in:

Wähle eine der folgenden:

  • A fourfold decrease of static pressure.

  • A fourfold increase of static pressure.

  • A twofold increase of static pressure.

  • A double decrease of static pressure.

Erklärung

Frage 48 von 200

1

Flatter is the name of a phenomenon associated with:

Wähle eine der folgenden:

  • The occurrence of self-existing vibrations.

  • The formation of the lift force.

  • The formation of drag force.

  • Elevator/rudder/aileron reversal.

Erklärung

Frage 49 von 200

1

When air enters a channel with velocity "V" and the channel cross-sectional area changes, that velocity also changes:

Wähle eine der folgenden:

  • The velocity "V" increases at reduced cross-sectional area .

  • The velocity "V" changes as the static pressure changes.

  • The velocity "V" does not change at all.

  • The velocity "V" decreases at reduced cross-sectional area and increases at increased cross-sectional area.

Erklärung

Frage 50 von 200

1

Aerofoil thickness is:

Wähle eine der folgenden:

  • The greatest distance between the upper and the lower airfoil surfaces, perpendicular to its chord.

  • The average distance between the upper and lower airfoil surfaces.

  • The distance between the upper and the lower airfoil surfaces at 50% chord line (MAC).

  • The greatest distance between the upper airfoil surface and the chord line.

Erklärung

Frage 51 von 200

1

Im większa lepkość powietrza tym: The greatest distance between. The bigger air viscosity:

Wähle eine der folgenden:

  • Opór tarcia większy, a warstwa przyścienna grubsza. The greater the drag and the thicker the boundary layer.

  • Opór tarcia mniejszy, a warstwa przyścienna cieńsza. The smaller the drag and the thinner the boundary layer.

  • Opór tarcia większy, a warstwa przyścienna cieńsza. The greater the drag and the thinner the boundary layer.

  • Opór tarcia mniejszy, a warstwa przyścienna grubsza. The smaller the drag and the thicker the boundary layer.

Erklärung

Frage 52 von 200

1

The existence of steerring control surfaces on the airframe causes mainly:

Wähle eine der folgenden:

  • Additional drag caused by slots between those surfaces and wings.

  • Induced drag.

  • Wave drag.

  • Skin friction drag.

Erklärung

Frage 53 von 200

1

What is a "flettner"?

Wähle eine der folgenden:

  • Balance tab.

  • Anti-balance tab.

  • Trim tab.

  • Trimmer .

Erklärung

Frage 54 von 200

1

How does the speed have to change in a balanced turn in order to increase the radious four times (keeping the same bank angle)?

Wähle eine der folgenden:

  • Double.

  • Increase 4 times.

  • Increase 8 times.

  • Reduce 4 times.

Erklärung

Frage 55 von 200

1

What is the name of a tab, which position may be independently changed during the flight?

Wähle eine der folgenden:

  • Trim tab.

  • Flettner.

  • Anti-balance tab.

  • Balance tab.

Erklärung

Frage 56 von 200

1

What is the name of the point at which the airflow changes from laminar to turbulent?

Wähle eine der folgenden:

  • Separation Point.

  • Stagnation Point.

  • Pressure Point.

  • Turbulent point.

Erklärung

Frage 57 von 200

1

Jak nazywa się wykres przedstawiający zależność współczynnika siły nośnej Cz od współczynnika oporu Cx statku powietrznego? What is the name of the graph showing the dependence between coefficients of lift CL and drag CD of the aircraft?

Wähle eine der folgenden:

  • Biegunowa. The Drag Polar.

  • Krzywa doskonałości. Airfoil fineness curve.

  • Biegunowa prędkości. Polar speed curve.

  • Wykres sprawności. Chart performance.

Erklärung

Frage 58 von 200

1

What is the aircraft's VNE?

Wähle eine der folgenden:

  • Never Exceed Speed.

  • Cruising speed.

  • Economic speed.

  • Optimal speed.

Erklärung

Frage 59 von 200

1

What are the SI units and symbols of mass, length and time?

Wähle eine der folgenden:

  • Kilogram (kg), meter (m) and second (sec).

  • Kilogram (kg), kilometer (km) and second (sec).

  • Kilogram (kg), nautical mile (nm) and hour (h).

  • Ton (t), meter (m) and minutes (min).

Erklärung

Frage 60 von 200

1

What are the SI units and symbols of force, pressure and temperature?

Wähle eine der folgenden:

  • Newton (N), Pascal (Pa), Kelvin (K).

  • Dyna (D), Bar (b), the degree Celsius (° C).

  • Pond (Po), atmosphere (at), degree Fahrenheit (° F).

  • Kilogram-force (kG), atmosphere (at), Kelvin (K).

Erklärung

Frage 61 von 200

1

What is the pressure of 1000 hPa in SI basic units?

Wähle eine der folgenden:

  • 100000 N/m.

  • 1000000 N/m.

  • 1000 N/m.

  • 10000 N/m.

Erklärung

Frage 62 von 200

1

How will the radius of a balanced turn change if the speed doubles at the constant bank angle?

Wähle eine der folgenden:

  • Increases 4 times.

  • Increases 2 times.

  • Increases 8 times.

  • Does not change.

Erklärung

Frage 63 von 200

1

How does the density altitude change when the air temperature is higher than ISA ?

Wähle eine der folgenden:

  • Increases.

  • Slightly decreases.

  • Does not change.

  • Decreases inversly proportional to the relative density sigma.

Erklärung

Frage 64 von 200

1

What is the difference between flat and steep spin?

Wähle eine der folgenden:

  • Greater angular change of direction in a flat spin.

  • Greater angular change of direction in a steep spin.

  • Higher rate of descent in a flat spin.

  • During the spin the pilot does not see any difference.

Erklärung

Frage 65 von 200

1

What is the standard ISA air pressure at sea level expressed in mmHg (corresponds to po = 1013.25 hPa)?

Wähle eine der folgenden:

  • 760 mm Hg.

  • 800 mm Hg.

  • 750 mm Hg.

  • 860 mm Hg.

Erklärung

Frage 66 von 200

1

What is the name of a ratio of static pressure at any height to the standard ISA pressure at sea level - delta = p/po?

Wähle eine der folgenden:

  • Relative pressure.

  • Standard pressure.

  • Modulal pressure.

  • The Hypocrite's Number.

Erklärung

Frage 67 von 200

1

What is the name of a the ratio of air density at any height to the standard (standard) density at sea level - sigma = rho/ rho o?

Wähle eine der folgenden:

  • The relative air density.

  • Laplace's constant.

  • The M/S ratio.

  • The Piccard's ratio.

Erklärung

Frage 68 von 200

1

What is the name of a ratio of air temperature at any altitude, expressed in Kelvin (K) to the reference temperature at sea level, also expressed in Kelvin (K) - Theta = T / To?

Wähle eine der folgenden:

  • The dimensionless relative temperature.

  • The absolute temperature.

  • The Don Pedro's constant.

  • The d'Amore coefficient.

Erklärung

Frage 69 von 200

1

What is the reference (standard) static pressure at sea level?

Wähle eine der folgenden:

  • After = 101325 N / m = 1013.25 hPa

  • After = 100000 N / m = 1000.00 hPa.

  • After = 111325 N / m = 1113.25 hPa.

  • After = 100025 N / m = 1000.25 hPa.

Erklärung

Frage 70 von 200

1

What is the reference (standard) air temperature at sea level expressed in Kelvins (K)?

Wähle eine der folgenden:

  • To = 288 K.

  • To = 258 K.

  • To = 277 K.

  • To = 301 K.

Erklärung

Frage 71 von 200

1

What is the reference (standard) air density at sea level expressed in kg/m2?

Wähle eine der folgenden:

  • rho o = 1.2255 kg/m2.

  • rho o = 1.0000 kg/m2.

  • rho o = 1.0255 kg/m2.

  • rho o = 1.2000 kg/m2.

Erklärung

Frage 72 von 200

1

What is the reference (standard) air temperature at sea level expressed in degrees Celsius (deg. C) ?

Wähle eine der folgenden:

  • t = 15 deg. C

  • t = 10 deg. C

  • t = 20 deg. C

  • 16.5 deg. C

Erklärung

Frage 73 von 200

1

What relationship exists between the air temperature t expressed in degrees Celsius (deg. C) and temperature T expressed in Kelvins (K)?

Wähle eine der folgenden:

  • T = t + 273.

  • T = t + 233.

  • T = t + 283.

  • T = t + 373.

Erklärung

Frage 74 von 200

1

What are the main features of a thick profile compared to a thinner one at the same velocity of an airflow?

Wähle eine der folgenden:

  • Higher drag and higher lift coefficient.

  • Higher drag and lower lift coefficient.

  • Higher drag and the same lift coefficient.

  • The same drag and higher lift coefficient.

Erklärung

Frage 75 von 200

1

What are the parameters used to describe the physical condition of the air?

Wähle eine der folgenden:

  • Static pressure, temperature and density.

  • Humidity and dynamic pressure.

  • Temperature, density and kinematic viscosity.

  • The content proportions of nitrogen and oxygen.

Erklärung

Frage 76 von 200

1

What are the prefixes of the SI units that mean the multiplication by 10, 100 and 1000?

Wähle eine der folgenden:

  • Deka-(da), hecto-(h), kilo-(k).

  • Kilo-(k), mega-(m), deca-(da).

  • The decision-(dc), hecto-(h), mega-(M).

  • Mega-(M), giga-(G), pico-(p).

Erklärung

Frage 77 von 200

1

What data is needed to calculate the load factor "n" in a balanced turn?

Wähle eine der folgenden:

  • It is enough to know the bank angle.

  • We need to know the speed and bank angle.

  • We need to know the turn radius and bank angle.

  • We need to know the speed, turn radius and bank angle.

Erklärung

Frage 78 von 200

1

What is purpose of "lift ugmentation systems" (flaps, slats, spoilers, etc.)?

Wähle eine der folgenden:

  • They change the aerodynamic coefficients in order to change the aircraft's performance (eg. approach speed).

  • They increase the maximum lift.

  • They increase the aicraft's airspeed.

  • They improve the aircraft's performance and therefore the economy of an aircraft.

Erklärung

Frage 79 von 200

1

What is the name of the instrument that measures the actual height or distance of an aircraft from the ground?

Wähle eine der folgenden:

  • The Radio altimeter (radar).

  • The pressure altimeter.

  • The optical rangefinder.

  • The DME.

Erklärung

Frage 80 von 200

1

One of the measurement of dynamic stability of an object (airplane, helicopter, glider, hang-glider, etc.) is so called "half-time". What is it?

Wähle eine der folgenden:

  • The time that elapses from the disturbance from equilibrium until it decreases in half (50%).

  • The half-period time of fugoidal flucutations caused by the disturbance.

  • Absolute stability.

  • Absolute instability.

Erklärung

Frage 81 von 200

1

If the body displaced from an equilibrium by a short-term external force is moving with constant spedd, then that body exhibits:

Wähle eine der folgenden:

  • Neutral stability.

  • Dynamic stability.

  • Absolute stability.

  • Absolute instability.

Erklärung

Frage 82 von 200

1

If the body displaced from an equilibrium by a short-term external force is in constant accelerated motion, then that body exhibits:

Wähle eine der folgenden:

  • Absolute instability

  • Neutral stability.

  • Dynamic stability.

  • Absolute stability.

Erklärung

Frage 83 von 200

1

If we add separate drags of all parts of the airframe (eg. wings, fuselage, tail, etc.), then the obtained sum is:

Wähle eine der folgenden:

  • Less than the overall drag of the assembled airframe.

  • Greater than the overall drag of the assembled airframe.

  • Equal to the overall drag of the assembled airframe.

  • To answer correctly one needs additional data from a wind tunnel.

Erklärung

Frage 84 von 200

1

If you double the velocity, the lift force:

Wähle eine der folgenden:

  • Increases 4 times.

  • Increases 2 times.

  • Decreases 4 times.

  • Decreases 2 times.

Erklärung

Frage 85 von 200

1

If you double the velocity, the drag force:

Wähle eine der folgenden:

  • Increases 4 times.

  • Increases 2 times.

  • Decreases 4 times.

  • Decreases 2 times.

Erklärung

Frage 86 von 200

1

If you reduce the temperature of the airflow, without changing the angle of attack, wing area and flow rate then:

Wähle eine der folgenden:

  • Aerodynamic forces on the wing increase.

  • Aerodynamic forces on the wing decrease.

  • Aerodynamic forces on the wing will not change because they do not depend on temperature.

  • Wing glide ratio increases.

Erklärung

Frage 87 von 200

1

If we increase the surface of the horizontal stabilizer:

Wähle eine der folgenden:

  • Longitudinal static stability increases.

  • Longitudinal static stability decreases.

  • Longitudinal controllability increases.

  • Longitudinal controllability does not change.

Erklärung

Frage 88 von 200

1

Każde ciało ma swój własny, stały i niezmienny współczynnik oporu kształtu Cx kszt:

Wähle eine der folgenden:

  • Fałsz, współczynnik oporu kształtu zależy również od ustawienia ciała. False, the form drag coefficient also depends on the body placement relative to the airflow.

  • Zawsze prawda. Always true.

  • Fałsz, współczynnik oporu kształtu nie zależy od kształtu ciała. False, the form drag coefficient does not depend on the body placement relative to the airflow.

  • Prawda tylko dla profili lotniczych. True only for airfoils.

Erklärung

Frage 89 von 200

1

The angle of attack for which Cd is minimum is always:

Wähle eine der folgenden:

  • Less than the angle of attack for (Cl/Cd)max.

  • Less than the angle of attack for optimal Cd.

  • Equal the angle of attack for Cl = 0.

  • Greater than the angle of attack for Cl = 0.

Erklärung

Frage 90 von 200

1

Angle of attack of the airfoil profile which is concave-convex shaped, for which there is no induced drag created has the value:

Wähle eine der folgenden:

  • Negative.

  • Positive.

  • Zero

  • Critical.

Erklärung

Frage 91 von 200

1

Angle of attack of profile is the angle between:

Wähle eine der folgenden:

  • Geometrical profile chord and the direction of undisturbed airflow.

  • Aerodynamic profile chord and velocity vector.

  • Geometrical profile chord and direction of descent vector.

  • The mean camber line and velocity vector.

Erklärung

Frage 92 von 200

1

Angle between the chord line and the direction of undisturbed airflow is:

Wähle eine der folgenden:

  • Profile angle of attack.

  • Profile convergence angle.

  • Dihedral angle.

  • Sweepback angle.

Erklärung

Frage 93 von 200

1

When altitude indicated on the ground by the pressure altimeter is a pressure altitude equal to the elevation of the airport?

Wähle eine der folgenden:

  • When ambient air conditions are the same as specified in the International Standard Atmosphere table.

  • In the tropical conditions.

  • When the radio altimeter indicates 0.

  • In the arctic conditions.

Erklärung

Frage 94 von 200

1

Flaps are used to:

Wähle eine der folgenden:

  • Increase Czmax.

  • Reduce the drag force at low speeds.

  • Improve the controllability in the full range of angles of attack.

  • Improve the stability in the full range of angles of attack.

Erklärung

Frage 95 von 200

1

Compensation aerodynamic rudder is designed to:

Wähle eine der folgenden:

  • Reduce control forces.

  • Balance the control surface in neutral position.

  • It act as mass balance of control surface.

  • Increase control forces.

Erklärung

Frage 96 von 200

1

Aerodynamic compensation of rudder is also called aerodynamic balance of the rudder.

Wähle eine der folgenden:

  • TRUE.

  • FALSE.

  • True, but only if the rudder mass balance has not been applied.

  • True, but only if rudder trim tab has not been applied.

Erklärung

Frage 97 von 200

1

Flat spin is:

Wähle eine der folgenden:

  • More dangerous than the steep.

  • Slightly less dangerous than the steep.

  • Same dangerous as the steep spin.

  • A lot less dangerous than the steep.

Erklärung

Frage 98 von 200

1

Critical flutter speed is the speed for which:

Wähle eine der folgenden:

  • Vibration excitating forces are equal damping forces.

  • Vibration excitating forces are larger than the damping forces.

  • Vibration excitating forces are smaller than the damping forces.

  • Forces damping self- excited vibrations disappear.

Erklärung

Frage 99 von 200

1

Którą oś układu współrzędnych nazywamy osią pionową? Which axis is called normal axis?

Wähle eine der folgenden:

  • Oś OZ? OZ-axis?

  • Oś OX? OX-axis?

  • Oś OY? Axis OY?

  • Takiej nazwy nie używa się. Such names are not used.

Erklärung

Frage 100 von 200

1

Which axis of the coordinate system is called the longitudinal axis?

Wähle eine der folgenden:

  • OX-axis?

  • Axis OY?

  • OZ-axis?

  • Such names are not used.

Erklärung

Frage 101 von 200

1

Which axis is called the lateral axis?

Wähle eine der folgenden:

  • Axis OY?

  • OZ-axis?

  • Axis OX?

  • Such names are not used.

Erklärung

Frage 102 von 200

1

Which devices are not lift augmentation wing devices?

Wähle eine der folgenden:

  • Increasing Cz max by reducing induced air flow, such as winglets.

  • Acting against flow separation on upper wing side on small angle of attack.

  • Changing effective aerodynamic angle of attack.

  • Increasing wing surface.

Erklärung

Frage 103 von 200

1

What is a potential energy?

Wähle eine der folgenden:

  • The product of weight and body height - unit joule [J].

  • The product of mass and body height-unit joule [J].

  • The product of weight and body height-unit Watt [W].

  • The product of mass and body height-unit Watt [W].

Erklärung

Frage 104 von 200

1

The curve representing the shape of wings as seen from above is:

Wähle eine der folgenden:

  • The planform of the wing.

  • The outline of the profile.

  • The Mean Camber line.

  • The Mean Chord line.

Erklärung

Frage 105 von 200

1

The line connecting the most front points of aerofoil is:

Wähle eine der folgenden:

  • Leading edge.

  • Trailing edge.

  • The chord line.

  • The Mean Camber line.

Erklärung

Frage 106 von 200

1

The line connecting the most rear points of aerofoil is:

Wähle eine der folgenden:

  • Trailing edge.

  • Leading edge.

  • The chord line.

  • The Mean Camber line.

Erklärung

Frage 107 von 200

1

The line drawn equidistant between the upper and lower surfaces of an aerofoil is called:

Wähle eine der folgenden:

  • The Mean Camber line.

  • The Chord line.

  • Maximum Camber.

  • Maximum Thickness.

Erklärung

Frage 108 von 200

1

Flight takes place on the angle of attack, for which the coefficient of drag "Cx" is the minimum. As a result of a small increase in angle of attack:

Wähle eine der folgenden:

  • The percentage increase of "Cz" is greater than the percentage increase of "Cx".

  • The percentage increase of "Cx" is greater than the percentage increase of "Cz".

  • The percentage increase of "Cx" is the same as the percentage increase of "Cz".

  • L/D ratio of the airframe will not change.

Erklärung

Frage 109 von 200

1

"Frise" ailerons-type are used to:

Wähle eine der folgenden:

  • Neutralize adverse yaw.

  • Increase banking momentum.

  • Reduce skin friction drag.

  • Reduce form drag during aileron deflection.

Erklärung

Frage 110 von 200

1

"Frise" ailerons-type are used to:

Wähle eine der folgenden:

  • OX axis.

  • OY axis.

  • OZ axis.

  • OZ axis and OY axis.

Erklärung

Frage 111 von 200

1

The never exceed speed "VNE"is:

Wähle eine der folgenden:

  • The greatest speed with which you can make a flight in calm air.

  • Velocity, to which no restrictions in the use of the aircraft is provided according to its intended purpose.

  • The maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe loads.

  • The maximum flight speed in turbulent air.

Erklärung

Frage 112 von 200

1

Maximum effeciency of profile:

Wähle eine der folgenden:

  • Is a constant value characteristic for the profile and corresponds to the maximum Cz/Cx ratio.

  • Varies depending on the angle of attack.

  • Always increases with increasing angle of attack.

  • Always increases with decreasing angle of attack.

Erklärung

Frage 113 von 200

1

The maximum speed of flight in turbulent air is:

Wähle eine der folgenden:

  • VRA.

  • VNE.

  • VNO.

  • VA.

Erklärung

Frage 114 von 200

1

The maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load is determined as:

Wähle eine der folgenden:

  • VA.

  • VRA.

  • VNE.

  • VNO.

Erklärung

Frage 115 von 200

1

Lift augmentation is used to:

Wähle eine der folgenden:

  • Increase Czmax.

  • Reduce drag force at low speeds.

  • Improve the controllability in the full range of angles of attack.

  • Improve the stability of the full range of angles of attack.

Erklärung

Frage 116 von 200

1

The minimum value of Cx coefficient we can obtain for the angle of attack equal 0°.

Wähle eine der folgenden:

  • Is true only for symmetric profiles.

  • Always true.

  • Is always false.

  • True but only for asymmetrical profiles.

Erklärung

Frage 117 von 200

1

Aerodynamic momentum measured from the aerodynamic center in flight speed range:

Wähle eine der folgenden:

  • Almost does not depend on the angle of attack, but it is proportional to the square of airspeed.

  • Is proportional to the square of the angle of attack and flight speed.

  • Almost does not depend on the angle of attack and flight speed.

  • Is constant and does not depend on the angle of attack and flight speed.

Erklärung

Frage 118 von 200

1

Aileron adverse yaw is because:

Wähle eine der folgenden:

  • Drag of aileron deflected downwards is greater than the drag of aileron deflected upwards.

  • Drag of aileron deflected downwards is lower than the drag of aileron deflected upwards.

  • Aileron deflection is accompanied by a hinge momentum, which causes the the adverse yaw.

  • Aileron deflection is accompanied by increase of induced drag.

Erklärung

Frage 119 von 200

1

On the lower surface of the wing air flow is deflected towards wing tip:

Wähle eine der folgenden:

  • The greater angle when closer to the wing tip.

  • The greater angle when closer to the center of the wing.

  • At constant angle at any wing point, but it depends on the angle of attack.

  • At constant angle at any wing point, but it depends on the speed of flight.

Erklärung

Frage 120 von 200

1

On the upper surface of the wing air flow is deflected towards wing root:

Wähle eine der folgenden:

  • The greater angle when the angle of attack is greater.

  • The smaller angle when the angle of attack is greater.

  • At constant angle at any wing point, but it depends on the angle of attack.

  • At constant angle at any wing point, but it depends on the speed of flight.

Erklärung

Frage 121 von 200

1

At what altitude, density of the air in ISA atmosphere is equal to one-fourth of the ISA density at sea level?

Wähle eine der folgenden:

  • 12200 m.

  • 11000 m.

  • 10000 m.

  • 13330 m.

Erklärung

Frage 122 von 200

1

At what altitude, density of the air in ISA atmosphere is equal to the ISA density at sea level?

Wähle eine der folgenden:

  • 0 m.

  • 100m.

  • 105m

  • 17,5 m.

Erklärung

Frage 123 von 200

1

At what altitude, density of the air in ISA atmosphere is equal to half of the ISA density at sea level?

Wähle eine der folgenden:

  • FL180

  • FL250

  • FL100

  • FL050

Erklärung

Frage 124 von 200

1

On what altitude pressure is equal to half of pressure at sea level in ISA atmosphere?

Wähle eine der folgenden:

  • FL180.

  • FL250.

  • FL100.

  • FL050.

Erklärung

Frage 125 von 200

1

Air flow around the wing is deflected towards:

Wähle eine der folgenden:

  • Deflected towards the wing root on the upper surface - Deflected towards the wing tip on the lower surface. E1633+SUM(SUM(D494:D1632))

  • Deflected towards the wing root on the lower surface - deflected towards the wing tip on the upper surface.

  • Deflected towards the wing root on the lower and upper surface.

  • Deflected towards the wing tip on the lower and upper surface.

Erklärung

Frage 126 von 200

1

The maximum distance between the upper and lower surfaces of the aerofoil is:

Wähle eine der folgenden:

  • Maximum Thickness.

  • Height of profile.

  • Thickness Chord Ratio.

  • Profile height ratio.

Erklärung

Frage 127 von 200

1

The highest speed at which you can fly in calm air is:

Wähle eine der folgenden:

  • VNE.

  • VNO.

  • VA.

  • VRA.

Erklärung

Frage 128 von 200

1

Momentum relative to normal, which arises from the aileron deflection by the same angle in opposite directions is called:

Wähle eine der folgenden:

  • Adverse yaw.

  • Roll momentum.

  • Dutch roll.

  • Aileron hinge moment.

Erklärung

Frage 129 von 200

1

Niestateczność holendrowania to jeden z rodzajów niestateczności: Dutch roll is one of the types of instability:

Wähle eine der folgenden:

  • Dynamicznej bocznej. Directional dynamic.

  • Statycznej kierunkowej. Directional static.

  • Dynamicznej poprzecznej. Lateral dynamic.

  • Dynamicznej kierunkowej. Lateral static.

Erklärung

Frage 130 von 200

1

Niestateczność spiralna to jeden z rodzajów niestateczności: Spiral instability is one of types of instability:

Wähle eine der folgenden:

  • Dynamicznej bocznej. Lateral dynamic.

  • Statycznej podłużnej. Directional static.

  • Dynamicznej poprzecznej. Directional dynamic.

  • Dynamicznej kierunkowej. Lateral static.

Erklärung

Frage 131 von 200

1

Slightly increase of the angle of attack in range just below maximum angle of attack causes:

Wähle eine der folgenden:

  • Increase of the "Cx "and the "Cz".

  • Decrease of the "Cx "and the "Cz".

  • Increase of the "Cx" and decrease of the "Cz".

  • Increase of the "Cz" and decrease of the "Cx".

Erklärung

Frage 132 von 200

1

Wing icing causes:

Wähle eine der folgenden:

  • Increase of the minimum speed.

  • Increase of the lift force.

  • Decrease of the rate of descent.

  • Decrease of the drag.

Erklärung

Frage 133 von 200

1

Airframe rotation around OX axis is realized through:

Wähle eine der folgenden:

  • Aileron.

  • Elevator.

  • Rudder.

  • Flaps.

Erklärung

Frage 134 von 200

1

Airframe rotation around OY axis is realized through:

Wähle eine der folgenden:

  • Elevator.

  • Rudder.

  • Flaps.

  • Ailerons.

Erklärung

Frage 135 von 200

1

Airframe rotation around OZ axis is realized through:

Wähle eine der folgenden:

  • Rudder.

  • Flaps.

  • Ailerons.

  • Elevator.

Erklärung

Frage 136 von 200

1

Opór ciała poruszającego się w powietrzu zależy od: Induced drag increases when:

Wähle eine der folgenden:

  • Współczynnika oporu, powierzchni odniesienia, gęstości powietrza kwadratu prędkości lotu. Wing aspect ratio decreases .

  • Współczynnika siły nośnej, oporu kształtu i powierzchni nośnej.Wing span increases.

  • Współczynnika oporu i ciśnienia całkowitego.Profile chord decreases.

  • Mocy silnika i prędkości lotu. Engine power and airspeed.

Erklärung

Frage 137 von 200

1

Opór indukowany wzrasta, gdy: Induced drag increases when:

Wähle eine der folgenden:

  • Maleje wydłużenie płata. Wing aspect ratio decreases.

  • Wzrasta rozpiętość skrzydła. Wing span increases.

  • Maleje cięciwa profilu. Profile chord decreases.

  • Maleje grubość profilu. Profile thickness decreases.

Erklärung

Frage 138 von 200

1

Interference drag is caused by:

Wähle eine der folgenden:

  • The fact that airflow is greatly disturbed where various components join togeather.

  • Interference between slot drag from various airframe parts.

  • Formation of vortices at wing tips.

  • Wave interference in subsonic flows.

Erklärung

Frage 139 von 200

1

Form drag depends only on the shape of the body:

Wähle eine der folgenden:

  • False, form drag also depends on the body position in airflow.

  • Always true.

  • False, form drag does not depend on the shape of the body

  • Is true only for the airfoil.

Erklärung

Frage 140 von 200

1

Aerofoil skin friction drag in cruise flight angles of attack is the smallest when the airflow is:

Wähle eine der folgenden:

  • Laminar.

  • Turbulent.

  • Spanwise.

  • Lilienthal.

Erklärung

Frage 141 von 200

1

Skin friction drag of laminar airflow compared to turbulent air flow is:

Wähle eine der folgenden:

  • Lower.

  • Is always higher.

  • The same for a perfectly clean surface, in other cases higher.

  • Always the same.

Erklärung

Frage 142 von 200

1

Drag which is due to vortices at wing tips caused by equalizing air pressure on the upper and lower surfaces is called:

Wähle eine der folgenden:

  • Induced drag.

  • Interference drag.

  • Wave resistance.

  • Rotational drag.

Erklärung

Frage 143 von 200

1

All-moving tailplane is a horizontal stabilizer and elevator:

Wähle eine der folgenden:

  • TRUE.

  • FALSE.

  • True, but only if the airframe is statically unstable.

  • True, but only if the airframe is dynamically unstable.

Erklärung

Frage 144 von 200

1

What will happen after exceeding speed which is limited by wing torsional rigidity:

Wähle eine der folgenden:

  • Wings will twist (critical damage).

  • Flutter.

  • Buffeting.

  • Ailerons reversal.

Erklärung

Frage 145 von 200

1

After aileron deflection at high speed arise:

Wähle eine der folgenden:

  • Wing twisting momentum, which causes an increase in wing angle of attack.

  • Wing twisting momentum, which reduces the wing angle of attack.

  • An additional lift force, which causes only bending of the wings, without twist.

  • An additional lift force, which causes only a roll, with no effect on the twisting and bending the wing.

Erklärung

Frage 146 von 200

1

During spin entry, the wing, which has higher angle of attack:

Wähle eine der folgenden:

  • Produces less lift than the wing with smaller angle of attack.

  • Produces more lift than the wing with smaller angle of attack.

  • Produces the lift as the wing with smaller angle of attack.

  • Does not produce lift, but only drag.

Erklärung

Frage 147 von 200

1

Położenie środka parcia na profilu klasycznym niesymetrycznym wraz ze wzrostem kąta natarcia: The location of Centre of Pressure on asymmetrical aerofoil withincreasing angle of attack:

Wähle eine der folgenden:

  • Przesuwa się do przodu. Moves forward.

  • Przesuwa się do tyłu. Moves aft.

  • Jest stałe i nie zależy od prędkości lotu. Is constant and does not depend on flight speed.

  • Jest stałe, ale zależy od prędkości lotu. Is constant, but depends on the flight speed.

Erklärung

Frage 148 von 200

1

Położenie środka parcia na profilu samostatecznym wraz ze wzrostem kąta natarcia: The location of Centre of Pressure on reflex-cambered aerofoil withincreasing angle of attack:

Wähle eine der folgenden:

  • Przesuwa się do tyłu. Moves aft.

  • Jest stałe. Is constant.

  • Przesuwa się do przodu. Moves forward.

  • Jest stałe, ale zależy od prędkości lotu. Is constant, but depends on the flight speed.

Erklärung

Frage 149 von 200

1

Poszerzacze stosuje się w celu: Fowler flaps are used to:

Wähle eine der folgenden:

  • Zmniejszenia Vmin. Reduce Vmin.

  • Zmniejszenia siły oporu na małych prędkościach. Reduce drag at low speed.

  • Poprawienia sterowności w pełnym zakresie kątów natarcia. Improve the controllability in the full range of angles of attack.

  • Poprawienia stateczności w pełnym zakresie kątów natarcia. Improve the stability of the full range of angles of attack.

Erklärung

Frage 150 von 200

1

Powierzchnia nośna skrzydła to: Wing area which generates lift is:

Wähle eine der folgenden:

  • Powierzchnia ograniczona obrysem skrzydła. Wing planform.

  • Powierzchnia dolnej płaszczyzny skrzydła. The lower surface of the wing.

  • Iloczyn rozpiętości skrzydła i szerokości profilu S=b c. Product of wing span and chord.

  • Iloczyn średniej cięciwy geometrycznej i wydłużenia skrzydła S=l Cśr. Product of the Mean Geometric Chord and wing aspect ratio.

Erklärung

Frage 151 von 200

1

The reson of skid in turn can be:

Wähle eine der folgenden:

  • Too small bank angle or too high angular velocity.

  • Too high bank angle or too small angular velocity.

  • Too high bank angle or too high angular velocity.

  • Too small bank angle or too small angular velocity.

Erklärung

Frage 152 von 200

1

The reson of slip in turn can be:

Wähle eine der folgenden:

  • Too high bank angle or too small angular velocity

  • Too high bank angle or too high angular velocity.

  • Too small bank angle or too small angular velocity.

  • Too small bank angle or too high angular velocity.

Erklärung

Frage 153 von 200

1

Design manoeuvering speed "Va" is:

Wähle eine der folgenden:

  • The maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load.

  • The maximum flight speed in turbulent air.

  • The maximum flight speed in calm air.

  • The speed to which all kinds of manoeuvres are permitted.

Erklärung

Frage 154 von 200

1

Speed for rough air operations, VRA is:

Wähle eine der folgenden:

  • The maximum flight speed in turbulent air.

  • The maximum flight speed in calm air.

  • The speed to which all kinds of manoeuvres are permitted.

  • The maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load.

Erklärung

Frage 155 von 200

1

Laminar aerofoil are those of which:

Wähle eine der folgenden:

  • The maximum thickness of the profile is in the range 50% -70% of the chord.

  • The maximum thickness of the profile is in the range of 20% -40% of the chord.

  • For medium and high-speed flow there is no transition from laminar to turbulent airflow.

  • The transition point from laminar flow around turbulence occurs in the posterior part of the profile.

Erklärung

Frage 156 von 200

1

Prosta łącząca środek krzywizny noska profilu z ostrzem (spływem) profilu to: The straight line joining leading and trailing edge of the wing aerofoil is:

Wähle eine der folgenden:

  • Cięciwa geometryczna profilu. The Chord line.

  • Cięciwa aerodynamiczna profilu. The Aerodynamic Chord line.

  • Średnia cięciwa aerodynamiczna. The mean aerodynamic chord.

  • Średnia grubość profilu. Average Thickness.

Erklärung

Frage 157 von 200

1

Dynamic stall differs from the static because during the dynamic stall:

Wähle eine der folgenden:

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

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

  • Aircraft remains dynamically stable.

  • Aircraft remains statically stable.

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Frage 158 von 200

1

Static stall is characterized by

Wähle eine der folgenden:

  • A slow change of angle of attack of the wing.

  • A rapid change of angle of attack of the wing.

  • Aircraft remains statically stable.

  • An increase in static stability.

Erklärung

Frage 159 von 200

1

Airflow around the wing tips due to equalizing pressure on the upper and lower surfaces creates vortices, which:

Wähle eine der folgenden:

  • Are greater when lift is greater.

  • Are greater when flight speed is higher.

  • Are greater when lift is samller.

  • Are greater when the attack angle of the wing is smaller.

Erklärung

Frage 160 von 200

1

Forward movement of Center of gravity:

Wähle eine der folgenden:

  • Decreases possibility of a flat spin entry.

  • Increases possibility of a flat spin entry.

  • Facilitates spin entry.

  • Makes recovery from a spin more difficult.

Erklärung

Frage 161 von 200

1

Aft movement of Center of gravity:

Wähle eine der folgenden:

  • Facilitates spin entry.

  • Makes spin entry more difficult.

  • Decreases possibility of a flat spin entry.

  • Facilitates spin recovery.

Erklärung

Frage 162 von 200

1

With increasing angle of incidence of the wings:

Wähle eine der folgenden:

  • Increases the difference of lift produced on both wings during the slip.

  • Lateral controlability is increasing.

  • Lateral static stability decreases.

  • Minimum speed decreases.

Erklärung

Frage 163 von 200

1

With increasing bank angle in coordinated turn G-force:

Wähle eine der folgenden:

  • Increases.

  • Decreases.

  • Does not change.

  • Gforce does not depend on bank angle, but on the airspeed.

Erklärung

Frage 164 von 200

1

Przyczyną zjawiska trzepotania usterzeń jest wystąpienie: The cause of buffeting is:

Wähle eine der folgenden:

  • Rezonansu pomiędzy drganiami zaburzonych strug zaskrzydłowych z drganiami własnymi powierzchni sterowych. A high-frequency instability, caused by airflow separation or shock wave oscillations from one object striking another. It is caused by a sudden impulse of load increasing.

  • Drgań giętno-skrętnych usterzenia. Torsional vibrations of control surfaces.

  • Flatteru usterzenia. Flutter of control surfaces.

  • Zjawiska zwanego dywergencją skrętną usterzenia. Phenomenon known as torsional divergence of control surfaces.

Erklärung

Frage 165 von 200

1

Increase of lift force on the elevator caused by the movement of yoke or stick is:

Wähle eine der folgenden:

  • Positive if we move yoke forward.

  • Negative if we move yoke forward.

  • Is always positive.

  • Is always negative.

Erklärung

Frage 166 von 200

1

The point on aerofoil, which is locatede the most aft to the direction of flight is:

Wähle eine der folgenden:

  • Trailing edge.

  • Leading edge.

  • Back edge.

  • Front edge.

Erklärung

Frage 167 von 200

1

The point on aerofoil, which is located the most forward to the direction of flight is:

Wähle eine der folgenden:

  • Leading edge.

  • Trailing edge.

  • Arrow.

  • Front edge.

Erklärung

Frage 168 von 200

1

The point, where the line of resultant aerodynamic force intersects the chord line is:

Wähle eine der folgenden:

  • Centre of Pressure.

  • Aerodynamic center.

  • Profile center.

  • Geometric center.

Erklärung

Frage 169 von 200

1

Point with respect to which the aerodynamic moment does not depend on the angle of attack (in a large range of changes of the angle of attack) is:

Wähle eine der folgenden:

  • Aerodynamic center.

  • Centre of Pressure.

  • Profile center.

  • Geometric centre.

Erklärung

Frage 170 von 200

1

The difference of increase of drag forces resulting from the aileron deflection by the same angle but in opposite directions gives:

Wähle eine der folgenden:

  • Adverse yaw.

  • A favorable deflection.

  • Adverse roll.

  • A favorable yaw.

Erklärung

Frage 171 von 200

1

Differential aileron deflection is used to:

Wähle eine der folgenden:

  • Neutralize adverse yaw.

  • Increase roll moment.

  • Reduce aileron hinge moment.

  • Reduce forces necessary for aileron deflection.

Erklärung

Frage 172 von 200

1

The movement of the aircraft during flight is described by:

Wähle eine der folgenden:

  • Three axes OX, OY, OZ.

  • Two axes OX and OY.

  • One axis OX.

  • Four axes OW, OX, OY, OZ.

Erklärung

Frage 173 von 200

1

Drag force of the wing moving down in the spin entry phase is:

Wähle eine der folgenden:

  • Greater than the drag force on the opposite wing.

  • Smaller than the drag force on the opposite wing.

  • The same as the drag force on the opposite wing.

  • Slightly less than the drag force on the opposite wing.

Erklärung

Frage 174 von 200

1

Siła wytworzona w wyniku różnicy ciśnień przed i za opływanym przez powietrze ciałem nosi nazwę: The force generated by the pressure difference before and after the body flowed by the air is:

Wähle eine der folgenden:

  • Siła oporu kształtu.Form drag.

  • Siła oporu tarcia. Skin friction drag.

  • Siła oporu indukowanego. Induced drag.

  • Siła oporu interferencyjnego. Interference drag.

Erklärung

Frage 175 von 200

1

Aerodynamic forces depend on the air density. How do they change when the density decreases?

Wähle eine der folgenden:

  • They decrease with the decreasing density

  • They increase inverse proportionally to the decreasing density.

  • They remain the same, regardless of air density.

  • They change proportionally to the square of the density.

Erklärung

Frage 176 von 200

1

Slats are used to:

Wähle eine der folgenden:

  • Increase Czmax.

  • Reduce the drag force at low speeds.

  • Improve the controllability in the full range of angles of attack.

  • Improve the stability of the full range of angles of attack.

Erklärung

Frage 177 von 200

1

Vertical stabilizer is primarily responsible for stability:

Wähle eine der folgenden:

  • Directional.

  • Longitudinal.

  • Lateral.

  • Vertical.

Erklärung

Frage 178 von 200

1

Horizontal stabilizer is primarily responsible for following stability:

Wähle eine der folgenden:

  • Longitudinal.

  • Lateral.

  • Horizontal.

  • Directional.

Erklärung

Frage 179 von 200

1

Stateczność dynamiczna boczna dotyczy: Dynamic lateral stability concerns:

Wähle eine der folgenden:

  • Odchylania i przechylania. Rolling and yawing.

  • Tylko pochylania. Only pitching.

  • Tylko przechylania. Only rolling.

  • Tylko odchylania. Only tilting.

Erklärung

Frage 180 von 200

1

Stateczność dynamiczna podłużna dotyczy: Longitudinal dynamic stability concerns:

Wähle eine der folgenden:

  • Pochylania. Pitching.

  • Przechylania.Rolling.

  • Odchylania. Yawing.

  • Odchylania i przechylania. Yawing and rolling.

Erklärung

Frage 181 von 200

1

Stateczność dynamiczną boczną można nazwać inaczej: Dutch roll concerns:

Wähle eine der folgenden:

  • Statecznością holendrowania. Directional and lateral stability.

  • Statecznością kierunkową. Directional stability.

  • Statecznością poprzeczną. Lateral stability.

  • Statecznością dynamiczną podłużną. Longitudinal dynamic stability.

Erklärung

Frage 182 von 200

1

Stateczność statyczna kierunkowa dotyczy: Static directional stability concerns:

Wähle eine der folgenden:

  • Odchylania. Yawing.

  • Odchylania i przechylania. Yawing and rolling.

  • Pochylania. Pitching.

  • Przechylania. Rolling.

Erklärung

Frage 183 von 200

1

Stateczność statyczna podłużna dotyczy: Static longitudinal stability concerns:

Wähle eine der folgenden:

  • Pochylania. Pitching.

  • Przechylania. Rolling.

  • Odchylania. Yawing.

  • Odchylania i przechylania. Yawing and rolling.

Erklärung

Frage 184 von 200

1

Stateczność statyczna poprzeczna dotyczy: Static Lateral Stability of concerns:

Wähle eine der folgenden:

  • Przechylania. Rolling.

  • Odchylania. Yawing.

  • Odchylania i przechylania. Yawing and rolling.

  • Pochylania. Pitching.

Erklärung

Frage 185 von 200

1

The ratio of the distance traveled in that time is:

Wähle eine der folgenden:

  • The average speed.

  • The average acceleration.

  • Instantaneous velocity.

  • Instantaneous acceleration.

Erklärung

Frage 186 von 200

1

The ratio of the surface of the wing span is:

Wähle eine der folgenden:

  • The Mean Geometric Chord.

  • Aspect ratio.

  • Convergence.

  • The Angle of Sweepback.

Erklärung

Frage 187 von 200

1

Change of the velocity at time t to time t is:

Wähle eine der folgenden:

  • The average acceleration.

  • Distance traveled by the body at time t.

  • Change in kinetic energy of the body.

  • Instantaneous acceleration.

Erklärung

Frage 188 von 200

1

Strzałka profilu to: Maximum Thickness:

Wähle eine der folgenden:

  • Największa odległość między linią szkieletową i cięciwą profilu. The maximum distance between the mean camber line and the chord line.

  • Najmniejsza odległość między linią szkieletową i cięciwą profilu. The minimum distance between the mean camber line and the chord line.

  • Największa odległość między górnym i dolnym obrysem profilu. The maximum distance between the upper and lower surface of airfoil.

  • Największa odległość między górnym obrysem profilu i cięciwą aerodynamiczną. The maximum distance between the upper surface of aerofoil and the mean aerodynamic chord.

Erklärung

Frage 189 von 200

1

Szkieletowa profilu to: The Mean Camber Line:

Wähle eine der folgenden:

  • Linia łącząca środki okręgów wpisanych w obrys profilu lotniczego. The line drawn equidistant between the upper and lower surfaces of an aerofoil.

  • Linia prosta łącząca nosek profilu z ostrzem (spływem) profilu lotniczego. A straight line connecting leading and trailing edge.

  • Linia łącząca noski profili płata lotniczego. A line connecting front points of aerofoil.

  • Linia łącząca ostrza profili płata lotniczego. A line connecting back points of aerofoil.

Erklärung

Frage 190 von 200

1

The average angular acceleration in a rotating movement is:

Wähle eine der folgenden:

  • Directly proportional to the increase of angular velocity during the measurement -inversely proportional to the time of measurement.

  • Directly proportional to the increase of angular velocity during the measurement -directly proportional to the time of measurement.

  • Inversely proportional to the increase of angular velocity during the measurement -inversely proportional to the time of measurement.

  • Inversely proportional to the increase of angular velocity during the measurement -directly proportional to the time of measurement.

Erklärung

Frage 191 von 200

1

The aerodynamic center is the point:

Wähle eine der folgenden:

  • With respect to which the aerodynamic moment does not depend on the angle of attack (in a large range of changes of the angle of attack).

  • Where the line of the resultant aerodynamic force intersects with the chord line.

  • Equidistant from the leading and the trailing edge.

  • Which in a large range of changes of the angle of attack coincides with the geometrical centre of aerofoil.

Erklärung

Frage 192 von 200

1

The aerodynamic center wiith the increase of angle of attack:

Wähle eine der folgenden:

  • In a large range of changes of the angle of attack does not change its position.

  • Moves forward.

  • Moves aft.

  • Does not change its position in the full range of changes the angle of attack.

Erklärung

Frage 193 von 200

1

Środek parcia to punkt: Center of Pressure (CP) is a point:

Wähle eine der folgenden:

  • W którym linia działania wypadkowej siły aerodynamicznej przecina cięciwę profilu. Positioned on chord aerodinamic force the intersection of the Total Reaction (Tr) of the chord line.

  • Względem którego moment aerodynamiczny nie zależy od kąta natarcia (w dużym przedziale zmian kąta natarcia). Reletive to the aerodynamic torque does not depend on the angle of attack (in a large range of changes in the angle of attack).

  • Równoodległy od noska i ostrza (spływu) profilu. At the same distance from the leading edge and the trailing edge of profile.

  • Który w dużym przedziale zmian kąta natarcia pokrywa się z geometrycznym środkiem profilu. Which has a large range of changes of the angle of attack and coincides with the geometrical profile.

Erklärung

Frage 194 von 200

1

Change suppression of flight parameters has an affect:

Wähle eine der folgenden:

  • Dynamic stability.

  • Static stability.

  • Increased static stability.

  • Neutral static stability.

Erklärung

Frage 195 von 200

1

Buffeting of the tail surfaces is otherwise known as:

Wähle eine der folgenden:

  • Buffeting.

  • Pre-stall buffet.

  • Ailerons flutter.

  • Tail flutter.

Erklärung

Frage 196 von 200

1

Ujemny skos skrzydła powoduje: The negative slant of wing causes:

Wähle eine der folgenden:

  • Zmniejszenie stateczności statycznej podłużnej. Reduction in the longitudinal static stability.

  • Zwiększenie stateczności statycznej podłużnej. Increase of the longitudinal static stability.

  • Zmniejszenie stateczności statycznej podłużnej na dodatnich kątach natarcia, a zwiększenie na ujemnych. Reduction of the static longitudinal stability at positive angles of attack, and the increase in the negative.

  • Zwiększenie stateczności statycznej podłużnej na dodatnich kątach natarcia, a zmniejszenie na ujemnych. Increase of the longitudinal static stability at positive angles of attack, and reduction on the negative.

Erklärung

Frage 197 von 200

1

Usterzenie kierunku zaprojektowane jest w celu obracania płatowca względem: Tail of the direction designed to rotate the airframe towards:

Wähle eine der folgenden:

  • ośi OZ›. Z- yaw axis.

  • ośi OX›. X- roll axis.

  • ośi OY›. Y- lateral axis.

  • ośi OX› i ośi OY›. X- roll axis and the y lateral axis.

Erklärung

Frage 198 von 200

1

Usterzenie wysokości zaprojektowane jest w celu obracania płatowca względem: Tail height designed to rotate the airframe towards:

Wähle eine der folgenden:

  • ośi OY›. Y- lateral axis.

  • ośi OZ›. Z- yaw axis.

  • ośi OX›. X- roll axis.

  • ośi OZ› i ośi OX›. Z- yaw axis and the x roll axis.

Erklärung

Frage 199 von 200

1

W celu zlikwidowania momentu oporowego lotek z reguły stosuje się: To eliminate of the aileron torque resistance as principle we use:

Wähle eine der folgenden:

  • Różnicowe wychylenie lotek. Lift augmentation system differential aileron deflection.

  • Dodatkowe wychylenia klapo-lotek. Extra-aileron deflection flap- aileron.

  • Wychylenie lotek o dokładnie ten sam kąt. Aileron deflection by exactly the same angle.

  • Jak najmniejsze wychylenia lotek. The lowest aileron deflection.

Erklärung

Frage 200 von 200

1

W codziennym życiu spotykamy się ze stanem równowagi: In everyday life we meet the state of stability:

Wähle eine der folgenden:

  • - stałej ; - obojętnej; - chwiejnej - fixed -neutral- unstable

  • - stałej ; - chwiejnej; - ruchomej - fixed -unstable- mobile

  • - stałej ; - obojętnej; - ruchomej - fixed- neutral- mobile

  • - nieobojętnej; - obojętnej; - chwiejnej -indifferent- indifferent- unstable

Erklärung