Test
Principles Of Flight
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Preguntas del test (200)
1 Are cambered aerofoils much more "sensitive" to contamination than laminar profiles?
- ANo.
- BYes.
- CNo, but only for small angles of attack.
- DYes, but only at high angles of attack.
2To prevent airleron flutter it is necessary to:
- AIncrease the bending rigidity of the wing and apply mass balance to the aileron.
- BApply aerodynamic balance - move the wing CoG closest to the axis of torsion.
- CApply balance tab and increase the torsional rigidity of the wing.
- DApply anti-balance tab and aileron mass balance.
3 To prevent bending-torsional flutter it is necessary to:
- AIncrease the torsional rigidity of the wing and move the wing CoG closest to the axis of torsion.
- BApply aerodynamic balance - move the wing CoG closest to the axis of torsion.
- CApply balance tab and increase the torsional rigidity of the wing.
- DApply anti-balance tab and aileron mass balance.
4 To prevent airleron reversal it is necessary to:
- AIncrease the torsional rigidity of the wing.
- BApply aerodynamic ballance.
- CApply balance tab.
- DApply anti-balance tab.
5 To prevent buffeting it is necessary to:
- AUse the T-tail configuration and carefully design wing-fuselage joint.
- BUse the T-tail configuration and trim tab.
- CUse trim tab and carefully design wing-fuselage joint.
- DIncrease the bending and torsional rigidity of the tailplane.
6 An aerodynamic leading edge is a line joining the points of airfoil where:
- AAirflow velocity is zero and the pressure equals stagnation pressure.
- BAirflow velocity is zero.
- CThe pressure is greater than the stagnation pressure.
- DAirflow velocity is zero and the pressure is at its minimum value.
7Lack of airlerons mass balance during high-speed flight is a direct cause of:
- AAileron flutter.
- BBending- torsional flutter.
- CAirleron reversal.
- DWing torsional divergence.
8 Buffeting means:
- AShaking of control surfaces.
- BBending- torsional vibrations.
- CAileron flatter.
- DTailplane flatter.
9An object moves with the speed V on a circular track. A double increase of the object's speed will cause the following:
- AAngular speed "Omega" doubles - centripetal accelaration "ar" increases four times.
- BAngular speed "Omega" doubles - centripetal accelaration "ar" doubles.
- CAngular speed "Omega" increases four times - centripetal accelaration "ar" increases four times.
- DAngular speed "Omega" increases four times - centripetal accelaration "ar" doubles.
10An object moves with the speed V on a circular track. A double increase of the track's radius will cause the following:
- AAngular speed "Omega" decreases by half - the object's full period path doubles - centripetal accelaration "ar" decreases by half.
- BAngular speed "Omega" decreases by half - the object's full period path decreases by half - centripetal accelaration "ar" decreases by half.
- CAngular speed "Omega" decreases by half - the object's full period path doubles - centripetal accelaration "ar" doubles.
- DAngular speed "Omega" decreases by half - the object's full period path double - centripetal accelaration "ar" stays constant.
11An object moves with the speed "V" on a circular track with radius "R". The resultant acceleration vector is always directed:
- ATowards the track center.
- BTowards the outside of the track.
- CSince the speed "V" is constant, no acceleration acts on the body.
- DTangent to the circle.
12 Static pressure at the separation point (change from laminar flow to turbulent flow) is:
- AMinimal on the upper surface and maximal on the bottom surface.
- BMaximal on the upper surface and mnimal at the bottom surface.
- CMinimal on the upper surface ana minimal on the bottom surface.
- DMaximal on the upper surface and maximal on the bottom surface.
13What does "the universal gas law" mean?
- ARelation between static pressure, density, temperature and gas constant p=rho*g*R*T [Pa].
- BRelation between the air pressure and its temperature
- CEquation of a balance between the air pressure and its humidity.
- DEquation of the balance between the air pressure and earth acceleration
14What dose the term " controllability " of a flying object ( plane, helicopter, glider, hang-glider etc) mean?
- AAbility of the object to "respond" to control impulses induced by the pilot.
- BAssurance that acrobatic exercises are permitted.
- CAssurance that the object's performance is as designed.
- DAssurance that the object is statically and dynamically stable.
15 What does "stagnation pressure" mean?
- AThe difference between the dynamic and static pressure.
- BThe highest measured pressure.
- CThe lowest measured pressure.
- DThe sum of a dynamic and static pressure.
16What is a "laminar flow"?
- AUndisturbed flow from the leading edge to the separation point.
- BUndisturbed flow along the entire chord, with air streams adhering to the profile.
- CDisturbed (turbulent) flow along the entire profile chord.
- DDisturbed (turbulent) flow along the entire profile chord, with maintained stream adherence to the profile.
17What does the aircraft (helicopter, glider, etc.) "absolute ceiling" mean?
- AThe highest theoretical altitude that the aircraft is able to climb.
- BAn altitude calculated in the design project of an aircraft.
- CThe altitude at which the aircraft still maintains the climbing ability of 0,5m/s.
- DThe altitude of the atmospere surrounding the Earth.
18 What does "static stability" of an object mean? (aircraft, helicopter, grinder, hang-grinder etc.)
- AA tendency (in a form of force or a moment) to return to the former equilibrium after a disturbance.
- BBalance condition.
- CNo reaction to balance disturbance.
- DObject static fluctuations around the lateral axis.
19What does "airfoil Center of Pressure" mean?
- AAn imaginable point on the chord of an aerofoil at with the resultant force (of all aerodynamic forces) act.
- BA drag force application point.
- CA point at which the pressure value is average.
- DA center of the profile chord line.
20What does the boundary layer mean"
- AA layer of air flowing around an arbitrary aircraft element in which the stream velocity changes from zero to free stream velocity.
- BA turbulent air region in the area of fuslage and other aircraft elements joints.
- CA part of an airstream flowing a part of aircraft with A-type flow.
- DA part of an airstream which changes from laminar to A-type flow.
21What is an "Aspect Ratio" of an aircraft or glider wing (or a propeller blade)?
- AThe ratio of wingspan to average chord length.
- BThe ratio of wing or blade length to the chord length at the base of it.
- CThe ratio of wingspan (rotor diameter) to the aircraft (helicopter) length.
- DThe ratio of mean aerodynamic chord to the wing or blade length.
22 What is the elevation of the airport?
- AThe physical elevation (altitude) of an airport apron above mean sea level according to ISA.
- BThe facade of an airport building.
- CThe surface of the runway.
- DThe slope of the main runway surface.
23 What is the air density?
- AAn air mass contained in a volume of 1m3.
- BThe opposite of the atmospheric viscosity.
- CThe number of molecules of oxygen and nitrogen in a 1cm3 volume.
- DThe weight of 1 m3 air.
24What is this the International Standard Atmosphere (ISA)?
- AA set of values considered as standard of static pressure (p), temperatures (t/T) and the air density (rho) at different heights.
- BA set of intormation about atmospheric parameters held at the UN headquarters in New York.
- CA set of intormation about atmospheric parameters held at the ICAO headquarters in Montreal.
- DA collection of air chemical composition at different heights.
25 What is it a pressure altitude above the airport level?
- AA reading of a pressure altimeter which is set to an airport pressure QFE.
- BA reading of a pressure altimeter which is set to sea level pressure QNH.
- CA reading of a radio altimeter.
- DThe airport elevation.
26What is pressure altitude above sea level?
- AA reading of a pressure altimeter when it is set to the current sea level pressure QNH.
- BThe airport elevation.
- CA reading of a pressure altimeter when it is set to the current airport pressure QFE.
- DA reading of a radio altimeter.
27 What is density altitude?
- ATheoretical height, where the air density is equal to the standard density according to ISA.
- BThe height according to international standard atmosphere (ISA).
- CThe airport elevation height corrected for the current air density.
- DThe pressure altitude corrected for humidity.
28What is the standard height?
- AA 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.
- BA reading of a standard radio altimeter.
- CThe airport elevation.
- DDensity altitude, corrected for ambient temperature.
29 Is there any connection between air static pressure (p), the absolute temperature (T) and density (rho)?
- AYes, 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.
- BYes, 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.
- CYes, expressed as a Crakow's form f [A, g, p, rho, T].
- DThere is no connection.
30Does the object (aircraft, helicopter, glider, hang-glider, etc.) statically unstable can be dynamically stable?
- ANo.
- BYes.
- CStatic stability is not important for the dynamic stability.
- DFixed-wing aircraft - yes, Rotorcraft - no.
31Does increase of stability affect controlability?
- AYes, controlability decreases.
- BYes, controlability increses.
- CNo, changes of stability do not affect controlability.
- DYes, at large angles of attack the controlability increases and at small decreases.
32 What is the difference between static stability and dynamic stability of an object (airplane, helicopter, glider, hang-glider etc.)?
- AThe static stability takes into account only tendency to return to the equilibrium state, the dynamic stability takes into account objects's movement type.
- BThere is no difference, the phenomenon is the same, just different names.
- CThey differ in the importance - dynamic stability is more important.
- DThe static stability concerns only balance on the ground, the dynamic stability - in-flight balance.
33What is the "static instability" of an object (airplane, helicopter, glider, hang-glider etc.)?
- AA tendency (in a form of force or a moment) to continue moving in the direction of displacement following a disturbance.
- BLack of any object reaction following a disturbance.
- CStatic fluctuations around the object lateral axis.
- DTrim balance condition.
34 What is the "neutral static stability" of an object (airplane, helicopter, glider, hang-glider etc.)?
- ALack of any object reacton following a disturbance.
- BA tendency (in a form of force or a moment) to return to equilibrium state following a disturbance.
- CStatic fluctuations around the object lateral axis.
- DTrim balance condition.
35What kind of profile doesn't create induced drag at zero angle of attack?
- ADouble convex symmetrical.
- BPlano-convex.
- CConcave-convex.
- DDouble convex asymmetrical.
36 For a constant accelerated motion, double increase of time at a constant acceleration causes:
- AA fourfold increase of the distance.
- BA double increase of the distance.
- CA double reduction of the distance.
- DA fourfold reduction of the distance.
37For a constant accelerated motion, double increase of acceleration within a constant time causes:
- AA double increase in the distance.
- BA fourfold increase in the distance.
- CA double reduction in the distance.
- DA fourfold reduction in the distance.
38 For a rectangular planform wing it is true that:
- AThe chord does not change along the wingspan.
- BThe chord decreases along the wingspan.
- CThe chord increases along the wingspan.
- DThe chord at first increases and then decreases along the wingspan.
39For the three wings with the same surface and the same wingspan, but with different planform (rectangular, tapered and elliptical), the Aspect Ratio is:
- AThe same for all planforms.
- BHighest for an elliptical planform and the smallest for a rectangular.
- CHighest for the rectangular planform and the smallest for an elliptical.
- DHighest for an elliptical planform and the smallest for the tapered.
40 For an established descent the following equation is true:
- APx=Q
- BPz=Q
- CQ=Q
- DPz=Px
41What is the "drag polar"?
- AA polar curve depicting the value of lift coefficient vs. drag coefficient.
- BA polar autorotation curve.
- CA chart of the power required.
- DA graph called "Titus Huber curve" in Poland.
42 The wing surface increasing devices are:
- AFowler flap and the leading edge flaps.
- BWinglets and trailing edge flaps.
- CSlots and the split flaps.
- DTrainling edge flaps and the split flaps.
43Devices that move the separation point aft on an airfoil upper surface are called:
- ASlats.
- BTrailing edge flaps.
- CSplit flaps.
- DFowler flap.
44Devices that increace the camber of an airfoil are called:
- ALeading edge flaps.
- BWinglets.
- CSlots.
- DAll answers are correct.
45 The backward sweep of a wing causes:
- AIncrease in the lateral static stability
- BReduction of the lateral static stability.
- CReduction of the lateral static stability at positive angles of attack and the increase at negative.
- DIncrease in the lateral static stability at positive angles of attack, and reduction at negative.
46Aaerofoil glide ratio:
- ADepends on the angle of attack.
- BIs a constant characteristic for the profile and corresponds to the (CL/CD)max.
- CAlways increases when increasing angle of attack.
- DAlways increases when decreasing angle of attack.
47 Doubling an airflow velocity in a closed tunnel will result in:
- AA fourfold decrease of static pressure.
- BA fourfold increase of static pressure.
- CA twofold increase of static pressure.
- DA double decrease of static pressure.
48Flatter is the name of a phenomenon associated with:
- AThe occurrence of self-existing vibrations.
- BThe formation of the lift force.
- CThe formation of drag force.
- DElevator/rudder/aileron reversal.
49 When air enters a channel with velocity "V" and the channel cross-sectional area changes, that velocity also changes:
- AThe velocity "V" increases at reduced cross-sectional area .
- BThe velocity "V" changes as the static pressure changes.
- CThe velocity "V" does not change at all.
- DThe velocity "V" decreases at reduced cross-sectional area and increases at increased cross-sectional area.
50Aerofoil thickness is:
- AThe greatest distance between the upper and the lower airfoil surfaces, perpendicular to its chord.
- BThe average distance between the upper and lower airfoil surfaces.
- CThe distance between the upper and the lower airfoil surfaces at 50% chord line (MAC).
- DThe greatest distance between the upper airfoil surface and the chord line.
51Im większa lepkość powietrza tym: The greatest distance between. The bigger air viscosity:
- AOpór tarcia większy, a warstwa przyścienna grubsza. The greater the drag and the thicker the boundary layer.
- BOpór tarcia mniejszy, a warstwa przyścienna cieńsza. The smaller the drag and the thinner the boundary layer.
- COpór tarcia większy, a warstwa przyścienna cieńsza. The greater the drag and the thinner the boundary layer.
- DOpór tarcia mniejszy, a warstwa przyścienna grubsza. The smaller the drag and the thicker the boundary layer.
52 The existence of steerring control surfaces on the airframe causes mainly:
- AAdditional drag caused by slots between those surfaces and wings.
- BInduced drag.
- CWave drag.
- DSkin friction drag.
53 What is a "flettner"?
- ABalance tab.
- BAnti-balance tab.
- CTrim tab.
- DTrimmer .
54How does the speed have to change in a balanced turn in order to increase the radious four times (keeping the same bank angle)?
- ADouble.
- BIncrease 4 times.
- CIncrease 8 times.
- DReduce 4 times.
55 What is the name of a tab, which position may be independently changed during the flight?
- ATrim tab.
- BFlettner.
- CAnti-balance tab.
- DBalance tab.
56 What is the name of the point at which the airflow changes from laminar to turbulent?
- ASeparation Point.
- BStagnation Point.
- CPressure Point.
- DTurbulent point.
57Jak 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?
- ABiegunowa. The Drag Polar.
- BKrzywa doskonałości. Airfoil fineness curve.
- CBiegunowa prędkości. Polar speed curve.
- DWykres sprawności. Chart performance.
58What is the aircraft's VNE?
- ANever Exceed Speed.
- BCruising speed.
- CEconomic speed.
- DOptimal speed.
59What are the SI units and symbols of mass, length and time?
- AKilogram (kg), meter (m) and second (sec).
- BKilogram (kg), kilometer (km) and second (sec).
- CKilogram (kg), nautical mile (nm) and hour (h).
- DTon (t), meter (m) and minutes (min).
60What are the SI units and symbols of force, pressure and temperature?
- ANewton (N), Pascal (Pa), Kelvin (K).
- BDyna (D), Bar (b), the degree Celsius (° C).
- CPond (Po), atmosphere (at), degree Fahrenheit (° F).
- DKilogram-force (kG), atmosphere (at), Kelvin (K).
61 What is the pressure of 1000 hPa in SI basic units?
- A100000 N/m.
- B1000000 N/m.
- C1000 N/m.
- D10000 N/m.
62How will the radius of a balanced turn change if the speed doubles at the constant bank angle?
- AIncreases 4 times.
- BIncreases 2 times.
- CIncreases 8 times.
- DDoes not change.
63How does the density altitude change when the air temperature is higher than ISA ?
- AIncreases.
- BSlightly decreases.
- CDoes not change.
- DDecreases inversly proportional to the relative density sigma.
64What is the difference between flat and steep spin?
- AGreater angular change of direction in a flat spin.
- BGreater angular change of direction in a steep spin.
- CHigher rate of descent in a flat spin.
- DDuring the spin the pilot does not see any difference.
65 What is the standard ISA air pressure at sea level expressed in mmHg (corresponds to po = 1013.25 hPa)?
- A760 mm Hg.
- B800 mm Hg.
- C750 mm Hg.
- D860 mm Hg.
66 What is the name of a ratio of static pressure at any height to the standard ISA pressure at sea level - delta = p/po?
- ARelative pressure.
- BStandard pressure.
- CModulal pressure.
- DThe Hypocrite's Number.
67What 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?
- AThe relative air density.
- BLaplace's constant.
- CThe M/S ratio.
- DThe Piccard's ratio.
68What 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?
- AThe dimensionless relative temperature.
- BThe absolute temperature.
- CThe Don Pedro's constant.
- DThe d'Amore coefficient.
69 What is the reference (standard) static pressure at sea level?
- AAfter = 101325 N / m = 1013.25 hPa
- BAfter = 100000 N / m = 1000.00 hPa.
- CAfter = 111325 N / m = 1113.25 hPa.
- DAfter = 100025 N / m = 1000.25 hPa.
70What is the reference (standard) air temperature at sea level expressed in Kelvins (K)?
- ATo = 288 K.
- BTo = 258 K.
- CTo = 277 K.
- DTo = 301 K.
71What is the reference (standard) air density at sea level expressed in kg/m2?
- Arho o = 1.2255 kg/m2.
- Brho o = 1.0000 kg/m2.
- Crho o = 1.0255 kg/m2.
- Drho o = 1.2000 kg/m2.
72What is the reference (standard) air temperature at sea level expressed in degrees Celsius (deg. C) ?
- At = 15 deg. C
- Bt = 10 deg. C
- Ct = 20 deg. C
- D16.5 deg. C
73What relationship exists between the air temperature t expressed in degrees Celsius (deg. C) and temperature T expressed in Kelvins (K)?
- AT = t + 273.
- BT = t + 233.
- CT = t + 283.
- DT = t + 373.
74What are the main features of a thick profile compared to a thinner one at the same velocity of an airflow?
- AHigher drag and higher lift coefficient.
- BHigher drag and lower lift coefficient.
- CHigher drag and the same lift coefficient.
- DThe same drag and higher lift coefficient.
75What are the parameters used to describe the physical condition of the air?
- AStatic pressure, temperature and density.
- BHumidity and dynamic pressure.
- CTemperature, density and kinematic viscosity.
- DThe content proportions of nitrogen and oxygen.
76What are the prefixes of the SI units that mean the multiplication by 10, 100 and 1000?
- ADeka-(da), hecto-(h), kilo-(k).
- BKilo-(k), mega-(m), deca-(da).
- CThe decision-(dc), hecto-(h), mega-(M).
- DMega-(M), giga-(G), pico-(p).
77What data is needed to calculate the load factor "n" in a balanced turn?
- AIt is enough to know the bank angle.
- BWe need to know the speed and bank angle.
- CWe need to know the turn radius and bank angle.
- DWe need to know the speed, turn radius and bank angle.
78What is purpose of "lift ugmentation systems" (flaps, slats, spoilers, etc.)?
- AThey change the aerodynamic coefficients in order to change the aircraft's performance (eg. approach speed).
- BThey increase the maximum lift.
- CThey increase the aicraft's airspeed.
- DThey improve the aircraft's performance and therefore the economy of an aircraft.
79What is the name of the instrument that measures the actual height or distance of an aircraft from the ground?
- AThe Radio altimeter (radar).
- BThe pressure altimeter.
- CThe optical rangefinder.
- DThe DME.
80 One of the measurement of dynamic stability of an object (airplane, helicopter, glider, hang-glider, etc.) is so called "half-time". What is it?
- AThe time that elapses from the disturbance from equilibrium until it decreases in half (50%).
- BThe half-period time of fugoidal flucutations caused by the disturbance.
- CAbsolute stability.
- DAbsolute instability.
81 If the body displaced from an equilibrium by a short-term external force is moving with constant spedd, then that body exhibits:
- ANeutral stability.
- BDynamic stability.
- CAbsolute stability.
- DAbsolute instability.
82 If the body displaced from an equilibrium by a short-term external force is in constant accelerated motion, then that body exhibits:
- AAbsolute instability
- BNeutral stability.
- CDynamic stability.
- DAbsolute stability.
83If we add separate drags of all parts of the airframe (eg. wings, fuselage, tail, etc.), then the obtained sum is:
- ALess than the overall drag of the assembled airframe.
- BGreater than the overall drag of the assembled airframe.
- CEqual to the overall drag of the assembled airframe.
- DTo answer correctly one needs additional data from a wind tunnel.
84 If you double the velocity, the lift force:
- AIncreases 4 times.
- BIncreases 2 times.
- CDecreases 4 times.
- DDecreases 2 times.
85If you double the velocity, the drag force:
- AIncreases 4 times.
- BIncreases 2 times.
- CDecreases 4 times.
- DDecreases 2 times.
86 If you reduce the temperature of the airflow, without changing the angle of attack, wing area and flow rate then:
- AAerodynamic forces on the wing increase.
- BAerodynamic forces on the wing decrease.
- CAerodynamic forces on the wing will not change because they do not depend on temperature.
- DWing glide ratio increases.
87If we increase the surface of the horizontal stabilizer:
- ALongitudinal static stability increases.
- BLongitudinal static stability decreases.
- CLongitudinal controllability increases.
- DLongitudinal controllability does not change.
88Każde ciało ma swój własny, stały i niezmienny współczynnik oporu kształtu Cx kszt:
- AFałsz, współczynnik oporu kształtu zależy również od ustawienia ciała. False, the form drag coefficient also depends on the body placement relative to the airflow.
- BZawsze prawda. Always true.
- CFałsz, współczynnik oporu kształtu nie zależy od kształtu ciała. False, the form drag coefficient does not depend on the body placement relative to the airflow.
- DPrawda tylko dla profili lotniczych. True only for airfoils.
89The angle of attack for which Cd is minimum is always:
- ALess than the angle of attack for (Cl/Cd)max.
- BLess than the angle of attack for optimal Cd.
- CEqual the angle of attack for Cl = 0.
- DGreater than the angle of attack for Cl = 0.
90 Angle of attack of the airfoil profile which is concave-convex shaped, for which there is no induced drag created has the value:
- ANegative.
- BPositive.
- CZero
- DCritical.
91Angle of attack of profile is the angle between:
- AGeometrical profile chord and the direction of undisturbed airflow.
- BAerodynamic profile chord and velocity vector.
- CGeometrical profile chord and direction of descent vector.
- DThe mean camber line and velocity vector.
92Angle between the chord line and the direction of undisturbed airflow is:
- AProfile angle of attack.
- BProfile convergence angle.
- CDihedral angle.
- DSweepback angle.
93When altitude indicated on the ground by the pressure altimeter is a pressure altitude equal to the elevation of the airport?
- AWhen ambient air conditions are the same as specified in the International Standard Atmosphere table.
- BIn the tropical conditions.
- CWhen the radio altimeter indicates 0.
- DIn the arctic conditions.
94 Flaps are used to:
- AIncrease Czmax.
- BReduce the drag force at low speeds.
- CImprove the controllability in the full range of angles of attack.
- DImprove the stability in the full range of angles of attack.
95Compensation aerodynamic rudder is designed to:
- AReduce control forces.
- BBalance the control surface in neutral position.
- CIt act as mass balance of control surface.
- DIncrease control forces.
96 Aerodynamic compensation of rudder is also called aerodynamic balance of the rudder.
- ATRUE.
- BFALSE.
- CTrue, but only if the rudder mass balance has not been applied.
- DTrue, but only if rudder trim tab has not been applied.
97 Flat spin is:
- AMore dangerous than the steep.
- BSlightly less dangerous than the steep.
- CSame dangerous as the steep spin.
- DA lot less dangerous than the steep.
98 Critical flutter speed is the speed for which:
- AVibration excitating forces are equal damping forces.
- BVibration excitating forces are larger than the damping forces.
- CVibration excitating forces are smaller than the damping forces.
- DForces damping self- excited vibrations disappear.
99Którą oś układu współrzędnych nazywamy osią pionową? Which axis is called normal axis?
- AOś OZ? OZ-axis?
- BOś OX? OX-axis?
- COś OY? Axis OY?
- DTakiej nazwy nie używa się. Such names are not used.
100Which axis of the coordinate system is called the longitudinal axis?
- AOX-axis?
- BAxis OY?
- COZ-axis?
- DSuch names are not used.
101 Which axis is called the lateral axis?
- AAxis OY?
- BOZ-axis?
- CAxis OX?
- DSuch names are not used.
102Which devices are not lift augmentation wing devices?
- AIncreasing Cz max by reducing induced air flow, such as winglets.
- BActing against flow separation on upper wing side on small angle of attack.
- CChanging effective aerodynamic angle of attack.
- DIncreasing wing surface.
103What is a potential energy?
- AThe product of weight and body height - unit joule [J].
- BThe product of mass and body height-unit joule [J].
- CThe product of weight and body height-unit Watt [W].
- DThe product of mass and body height-unit Watt [W].
104 The curve representing the shape of wings as seen from above is:
- AThe planform of the wing.
- BThe outline of the profile.
- CThe Mean Camber line.
- DThe Mean Chord line.
105 The line connecting the most front points of aerofoil is:
- ALeading edge.
- BTrailing edge.
- CThe chord line.
- DThe Mean Camber line.
106The line connecting the most rear points of aerofoil is:
- ATrailing edge.
- BLeading edge.
- CThe chord line.
- DThe Mean Camber line.
107The line drawn equidistant between the upper and lower surfaces of an aerofoil is called:
- AThe Mean Camber line.
- BThe Chord line.
- CMaximum Camber.
- DMaximum Thickness.
108Flight 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:
- AThe percentage increase of "Cz" is greater than the percentage increase of "Cx".
- BThe percentage increase of "Cx" is greater than the percentage increase of "Cz".
- CThe percentage increase of "Cx" is the same as the percentage increase of "Cz".
- DL/D ratio of the airframe will not change.
109 "Frise" ailerons-type are used to:
- ANeutralize adverse yaw.
- BIncrease banking momentum.
- CReduce skin friction drag.
- DReduce form drag during aileron deflection.
110 "Frise" ailerons-type are used to:
- AOX axis.
- BOY axis.
- COZ axis.
- DOZ axis and OY axis.
111The never exceed speed "VNE"is:
- AThe greatest speed with which you can make a flight in calm air.
- BVelocity, to which no restrictions in the use of the aircraft is provided according to its intended purpose.
- CThe maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe loads.
- DThe maximum flight speed in turbulent air.
112Maximum effeciency of profile:
- AIs a constant value characteristic for the profile and corresponds to the maximum Cz/Cx ratio.
- BVaries depending on the angle of attack.
- CAlways increases with increasing angle of attack.
- DAlways increases with decreasing angle of attack.
113The maximum speed of flight in turbulent air is:
- AVRA.
- BVNE.
- CVNO.
- DVA.
114 The maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load is determined as:
- AVA.
- BVRA.
- CVNE.
- DVNO.
115 Lift augmentation is used to:
- AIncrease Czmax.
- BReduce drag force at low speeds.
- CImprove the controllability in the full range of angles of attack.
- DImprove the stability of the full range of angles of attack.
116The minimum value of Cx coefficient we can obtain for the angle of attack equal 0°.
- AIs true only for symmetric profiles.
- BAlways true.
- CIs always false.
- DTrue but only for asymmetrical profiles.
117Aerodynamic momentum measured from the aerodynamic center in flight speed range:
- AAlmost does not depend on the angle of attack, but it is proportional to the square of airspeed.
- BIs proportional to the square of the angle of attack and flight speed.
- CAlmost does not depend on the angle of attack and flight speed.
- DIs constant and does not depend on the angle of attack and flight speed.
118 Aileron adverse yaw is because:
- ADrag of aileron deflected downwards is greater than the drag of aileron deflected upwards.
- BDrag of aileron deflected downwards is lower than the drag of aileron deflected upwards.
- CAileron deflection is accompanied by a hinge momentum, which causes the the adverse yaw.
- DAileron deflection is accompanied by increase of induced drag.
119 On the lower surface of the wing air flow is deflected towards wing tip:
- AThe greater angle when closer to the wing tip.
- BThe greater angle when closer to the center of the wing.
- CAt constant angle at any wing point, but it depends on the angle of attack.
- DAt constant angle at any wing point, but it depends on the speed of flight.
120 On the upper surface of the wing air flow is deflected towards wing root:
- AThe greater angle when the angle of attack is greater.
- BThe smaller angle when the angle of attack is greater.
- CAt constant angle at any wing point, but it depends on the angle of attack.
- DAt constant angle at any wing point, but it depends on the speed of flight.
121 At what altitude, density of the air in ISA atmosphere is equal to one-fourth of the ISA density at sea level?
- A12200 m.
- B11000 m.
- C10000 m.
- D13330 m.
122At what altitude, density of the air in ISA atmosphere is equal to the ISA density at sea level?
- A0 m.
- B100m.
- C105m
- D17,5 m.
123At what altitude, density of the air in ISA atmosphere is equal to half of the ISA density at sea level?
- AFL180
- BFL250
- CFL100
- DFL050
124On what altitude pressure is equal to half of pressure at sea level in ISA atmosphere?
- AFL180.
- BFL250.
- CFL100.
- DFL050.
125 Air flow around the wing is deflected towards:
- ADeflected towards the wing root on the upper surface - Deflected towards the wing tip on the lower surface. E1633+SUM(SUM(D494:D1632))
- BDeflected towards the wing root on the lower surface - deflected towards the wing tip on the upper surface.
- CDeflected towards the wing root on the lower and upper surface.
- DDeflected towards the wing tip on the lower and upper surface.
126The maximum distance between the upper and lower surfaces of the aerofoil is:
- AMaximum Thickness.
- BHeight of profile.
- CThickness Chord Ratio.
- DProfile height ratio.
127The highest speed at which you can fly in calm air is:
- AVNE.
- BVNO.
- CVA.
- DVRA.
128Momentum relative to normal, which arises from the aileron deflection by the same angle in opposite directions is called:
- AAdverse yaw.
- BRoll momentum.
- CDutch roll.
- DAileron hinge moment.
129Niestateczność holendrowania to jeden z rodzajów niestateczności: Dutch roll is one of the types of instability:
- ADynamicznej bocznej. Directional dynamic.
- BStatycznej kierunkowej. Directional static.
- CDynamicznej poprzecznej. Lateral dynamic.
- DDynamicznej kierunkowej. Lateral static.
130Niestateczność spiralna to jeden z rodzajów niestateczności: Spiral instability is one of types of instability:
- ADynamicznej bocznej. Lateral dynamic.
- BStatycznej podłużnej. Directional static.
- CDynamicznej poprzecznej. Directional dynamic.
- DDynamicznej kierunkowej. Lateral static.
131 Slightly increase of the angle of attack in range just below maximum angle of attack causes:
- AIncrease of the "Cx "and the "Cz".
- BDecrease of the "Cx "and the "Cz".
- CIncrease of the "Cx" and decrease of the "Cz".
- DIncrease of the "Cz" and decrease of the "Cx".
132Wing icing causes:
- AIncrease of the minimum speed.
- BIncrease of the lift force.
- CDecrease of the rate of descent.
- DDecrease of the drag.
133Airframe rotation around OX axis is realized through:
- AAileron.
- BElevator.
- CRudder.
- DFlaps.
134 Airframe rotation around OY axis is realized through:
- AElevator.
- BRudder.
- CFlaps.
- DAilerons.
135 Airframe rotation around OZ axis is realized through:
- ARudder.
- BFlaps.
- CAilerons.
- DElevator.
136Opór ciała poruszającego się w powietrzu zależy od: Induced drag increases when:
- AWspółczynnika oporu, powierzchni odniesienia, gęstości powietrza kwadratu prędkości lotu. Wing aspect ratio decreases .
- BWspółczynnika siły nośnej, oporu kształtu i powierzchni nośnej.Wing span increases.
- CWspółczynnika oporu i ciśnienia całkowitego.Profile chord decreases.
- DMocy silnika i prędkości lotu. Engine power and airspeed.
137 Opór indukowany wzrasta, gdy: Induced drag increases when:
- AMaleje wydłużenie płata. Wing aspect ratio decreases.
- BWzrasta rozpiętość skrzydła. Wing span increases.
- CMaleje cięciwa profilu. Profile chord decreases.
- DMaleje grubość profilu. Profile thickness decreases.
138 Interference drag is caused by:
- AThe fact that airflow is greatly disturbed where various components join togeather.
- BInterference between slot drag from various airframe parts.
- CFormation of vortices at wing tips.
- DWave interference in subsonic flows.
139 Form drag depends only on the shape of the body:
- AFalse, form drag also depends on the body position in airflow.
- BAlways true.
- CFalse, form drag does not depend on the shape of the body
- DIs true only for the airfoil.
140Aerofoil skin friction drag in cruise flight angles of attack is the smallest when the airflow is:
- ALaminar.
- BTurbulent.
- CSpanwise.
- DLilienthal.
141Skin friction drag of laminar airflow compared to turbulent air flow is:
- ALower.
- BIs always higher.
- CThe same for a perfectly clean surface, in other cases higher.
- DAlways the same.
142 Drag which is due to vortices at wing tips caused by equalizing air pressure on the upper and lower surfaces is called:
- AInduced drag.
- BInterference drag.
- CWave resistance.
- DRotational drag.
143 All-moving tailplane is a horizontal stabilizer and elevator:
- ATRUE.
- BFALSE.
- CTrue, but only if the airframe is statically unstable.
- DTrue, but only if the airframe is dynamically unstable.
144 What will happen after exceeding speed which is limited by wing torsional rigidity:
- AWings will twist (critical damage).
- BFlutter.
- CBuffeting.
- DAilerons reversal.
145 After aileron deflection at high speed arise:
- AWing twisting momentum, which causes an increase in wing angle of attack.
- BWing twisting momentum, which reduces the wing angle of attack.
- CAn additional lift force, which causes only bending of the wings, without twist.
- DAn additional lift force, which causes only a roll, with no effect on the twisting and bending the wing.
146 During spin entry, the wing, which has higher angle of attack:
- AProduces less lift than the wing with smaller angle of attack.
- BProduces more lift than the wing with smaller angle of attack.
- CProduces the lift as the wing with smaller angle of attack.
- DDoes not produce lift, but only drag.
147Położenie środka parcia na profilu klasycznym niesymetrycznym wraz ze wzrostem kąta natarcia: The location of Centre of Pressure on asymmetrical aerofoil withincreasing angle of attack:
- APrzesuwa się do przodu. Moves forward.
- BPrzesuwa się do tyłu. Moves aft.
- CJest stałe i nie zależy od prędkości lotu. Is constant and does not depend on flight speed.
- DJest stałe, ale zależy od prędkości lotu. Is constant, but depends on the flight speed.
148Położenie środka parcia na profilu samostatecznym wraz ze wzrostem kąta natarcia: The location of Centre of Pressure on reflex-cambered aerofoil withincreasing angle of attack:
- APrzesuwa się do tyłu. Moves aft.
- BJest stałe. Is constant.
- CPrzesuwa się do przodu. Moves forward.
- DJest stałe, ale zależy od prędkości lotu. Is constant, but depends on the flight speed.
149Poszerzacze stosuje się w celu: Fowler flaps are used to:
- AZmniejszenia Vmin. Reduce Vmin.
- BZmniejszenia siły oporu na małych prędkościach. Reduce drag at low speed.
- CPoprawienia sterowności w pełnym zakresie kątów natarcia. Improve the controllability in the full range of angles of attack.
- DPoprawienia stateczności w pełnym zakresie kątów natarcia. Improve the stability of the full range of angles of attack.
150Powierzchnia nośna skrzydła to: Wing area which generates lift is:
- APowierzchnia ograniczona obrysem skrzydła. Wing planform.
- BPowierzchnia dolnej płaszczyzny skrzydła. The lower surface of the wing.
- CIloczyn rozpiętości skrzydła i szerokości profilu S=b c. Product of wing span and chord.
- DIloczyn średniej cięciwy geometrycznej i wydłużenia skrzydła S=l Cśr. Product of the Mean Geometric Chord and wing aspect ratio.
151The reson of skid in turn can be:
- AToo small bank angle or too high angular velocity.
- BToo high bank angle or too small angular velocity.
- CToo high bank angle or too high angular velocity.
- DToo small bank angle or too small angular velocity.
152The reson of slip in turn can be:
- AToo high bank angle or too small angular velocity
- BToo high bank angle or too high angular velocity.
- CToo small bank angle or too small angular velocity.
- DToo small bank angle or too high angular velocity.
153 Design manoeuvering speed "Va" is:
- AThe maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load.
- BThe maximum flight speed in turbulent air.
- CThe maximum flight speed in calm air.
- DThe speed to which all kinds of manoeuvres are permitted.
154Speed for rough air operations, VRA is:
- AThe maximum flight speed in turbulent air.
- BThe maximum flight speed in calm air.
- CThe speed to which all kinds of manoeuvres are permitted.
- DThe maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load.
155Laminar aerofoil are those of which:
- AThe maximum thickness of the profile is in the range 50% -70% of the chord.
- BThe maximum thickness of the profile is in the range of 20% -40% of the chord.
- CFor medium and high-speed flow there is no transition from laminar to turbulent airflow.
- DThe transition point from laminar flow around turbulence occurs in the posterior part of the profile.
156Prosta łącząca środek krzywizny noska profilu z ostrzem (spływem) profilu to: The straight line joining leading and trailing edge of the wing aerofoil is:
- ACięciwa geometryczna profilu. The Chord line.
- BCięciwa aerodynamiczna profilu. The Aerodynamic Chord line.
- CŚrednia cięciwa aerodynamiczna. The mean aerodynamic chord.
- DŚrednia grubość profilu. Average Thickness.
157Dynamic stall differs from the static because during the dynamic stall:
- AThere is a rapid change in wing angle of attack.
- BThere is a slow change in wing angle of attack.
- CAircraft remains dynamically stable.
- DAircraft remains statically stable.
158Static stall is characterized by
- AA slow change of angle of attack of the wing.
- BA rapid change of angle of attack of the wing.
- CAircraft remains statically stable.
- DAn increase in static stability.
159Airflow around the wing tips due to equalizing pressure on the upper and lower surfaces creates vortices, which:
- AAre greater when lift is greater.
- BAre greater when flight speed is higher.
- CAre greater when lift is samller.
- DAre greater when the attack angle of the wing is smaller.
160Forward movement of Center of gravity:
- ADecreases possibility of a flat spin entry.
- BIncreases possibility of a flat spin entry.
- CFacilitates spin entry.
- DMakes recovery from a spin more difficult.
161Aft movement of Center of gravity:
- AFacilitates spin entry.
- BMakes spin entry more difficult.
- CDecreases possibility of a flat spin entry.
- DFacilitates spin recovery.
162With increasing angle of incidence of the wings:
- AIncreases the difference of lift produced on both wings during the slip.
- BLateral controlability is increasing.
- CLateral static stability decreases.
- DMinimum speed decreases.
163 With increasing bank angle in coordinated turn G-force:
- AIncreases.
- BDecreases.
- CDoes not change.
- DGforce does not depend on bank angle, but on the airspeed.
164Przyczyną zjawiska trzepotania usterzeń jest wystąpienie: The cause of buffeting is:
- ARezonansu 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.
- BDrgań giętno-skrętnych usterzenia. Torsional vibrations of control surfaces.
- CFlatteru usterzenia. Flutter of control surfaces.
- DZjawiska zwanego dywergencją skrętną usterzenia. Phenomenon known as torsional divergence of control surfaces.
165 Increase of lift force on the elevator caused by the movement of yoke or stick is:
- APositive if we move yoke forward.
- BNegative if we move yoke forward.
- CIs always positive.
- DIs always negative.
166 The point on aerofoil, which is locatede the most aft to the direction of flight is:
- ATrailing edge.
- BLeading edge.
- CBack edge.
- DFront edge.
167The point on aerofoil, which is located the most forward to the direction of flight is:
- ALeading edge.
- BTrailing edge.
- CArrow.
- DFront edge.
168The point, where the line of resultant aerodynamic force intersects the chord line is:
- ACentre of Pressure.
- BAerodynamic center.
- CProfile center.
- DGeometric center.
169Point 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:
- AAerodynamic center.
- BCentre of Pressure.
- CProfile center.
- DGeometric centre.
170The difference of increase of drag forces resulting from the aileron deflection by the same angle but in opposite directions gives:
- AAdverse yaw.
- BA favorable deflection.
- CAdverse roll.
- DA favorable yaw.
171Differential aileron deflection is used to:
- ANeutralize adverse yaw.
- BIncrease roll moment.
- CReduce aileron hinge moment.
- DReduce forces necessary for aileron deflection.
172The movement of the aircraft during flight is described by:
- AThree axes OX, OY, OZ.
- BTwo axes OX and OY.
- COne axis OX.
- DFour axes OW, OX, OY, OZ.
173Drag force of the wing moving down in the spin entry phase is:
- AGreater than the drag force on the opposite wing.
- BSmaller than the drag force on the opposite wing.
- CThe same as the drag force on the opposite wing.
- DSlightly less than the drag force on the opposite wing.
174Siła 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:
- ASiła oporu kształtu.Form drag.
- BSiła oporu tarcia. Skin friction drag.
- CSiła oporu indukowanego. Induced drag.
- DSiła oporu interferencyjnego. Interference drag.
175Aerodynamic forces depend on the air density. How do they change when the density decreases?
- AThey decrease with the decreasing density
- BThey increase inverse proportionally to the decreasing density.
- CThey remain the same, regardless of air density.
- DThey change proportionally to the square of the density.
176 Slats are used to:
- AIncrease Czmax.
- BReduce the drag force at low speeds.
- CImprove the controllability in the full range of angles of attack.
- DImprove the stability of the full range of angles of attack.
177Vertical stabilizer is primarily responsible for stability:
- ADirectional.
- BLongitudinal.
- CLateral.
- DVertical.
178 Horizontal stabilizer is primarily responsible for following stability:
- ALongitudinal.
- BLateral.
- CHorizontal.
- DDirectional.
179Stateczność dynamiczna boczna dotyczy: Dynamic lateral stability concerns:
- AOdchylania i przechylania. Rolling and yawing.
- BTylko pochylania. Only pitching.
- CTylko przechylania. Only rolling.
- DTylko odchylania. Only tilting.
180Stateczność dynamiczna podłużna dotyczy: Longitudinal dynamic stability concerns:
- APochylania. Pitching.
- BPrzechylania.Rolling.
- COdchylania. Yawing.
- DOdchylania i przechylania. Yawing and rolling.
181Stateczność dynamiczną boczną można nazwać inaczej: Dutch roll concerns:
- AStatecznością holendrowania. Directional and lateral stability.
- BStatecznością kierunkową. Directional stability.
- CStatecznością poprzeczną. Lateral stability.
- DStatecznością dynamiczną podłużną. Longitudinal dynamic stability.
182Stateczność statyczna kierunkowa dotyczy: Static directional stability concerns:
- AOdchylania. Yawing.
- BOdchylania i przechylania. Yawing and rolling.
- CPochylania. Pitching.
- DPrzechylania. Rolling.
183Stateczność statyczna podłużna dotyczy: Static longitudinal stability concerns:
- APochylania. Pitching.
- BPrzechylania. Rolling.
- COdchylania. Yawing.
- DOdchylania i przechylania. Yawing and rolling.
184Stateczność statyczna poprzeczna dotyczy: Static Lateral Stability of concerns:
- APrzechylania. Rolling.
- BOdchylania. Yawing.
- COdchylania i przechylania. Yawing and rolling.
- DPochylania. Pitching.
185The ratio of the distance traveled in that time is:
- AThe average speed.
- BThe average acceleration.
- CInstantaneous velocity.
- DInstantaneous acceleration.
186The ratio of the surface of the wing span is:
- AThe Mean Geometric Chord.
- BAspect ratio.
- CConvergence.
- DThe Angle of Sweepback.
187Change of the velocity at time t to time t is:
- AThe average acceleration.
- BDistance traveled by the body at time t.
- CChange in kinetic energy of the body.
- DInstantaneous acceleration.
188 Strzałka profilu to: Maximum Thickness:
- ANajwiększa odległość między linią szkieletową i cięciwą profilu. The maximum distance between the mean camber line and the chord line.
- BNajmniejsza odległość między linią szkieletową i cięciwą profilu. The minimum distance between the mean camber line and the chord line.
- CNajwiększa odległość między górnym i dolnym obrysem profilu. The maximum distance between the upper and lower surface of airfoil.
- DNajwiększa odległość między górnym obrysem profilu i cięciwą aerodynamiczną. The maximum distance between the upper surface of aerofoil and the mean aerodynamic chord.
189 Szkieletowa profilu to: The Mean Camber Line:
- ALinia łącząca środki okręgów wpisanych w obrys profilu lotniczego. The line drawn equidistant between the upper and lower surfaces of an aerofoil.
- BLinia prosta łącząca nosek profilu z ostrzem (spływem) profilu lotniczego. A straight line connecting leading and trailing edge.
- CLinia łącząca noski profili płata lotniczego. A line connecting front points of aerofoil.
- DLinia łącząca ostrza profili płata lotniczego. A line connecting back points of aerofoil.
190The average angular acceleration in a rotating movement is:
- ADirectly proportional to the increase of angular velocity during the measurement -inversely proportional to the time of measurement.
- BDirectly proportional to the increase of angular velocity during the measurement -directly proportional to the time of measurement.
- CInversely proportional to the increase of angular velocity during the measurement -inversely proportional to the time of measurement.
- DInversely proportional to the increase of angular velocity during the measurement -directly proportional to the time of measurement.
191The aerodynamic center is the point:
- AWith 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).
- BWhere the line of the resultant aerodynamic force intersects with the chord line.
- CEquidistant from the leading and the trailing edge.
- DWhich in a large range of changes of the angle of attack coincides with the geometrical centre of aerofoil.
192The aerodynamic center wiith the increase of angle of attack:
- AIn a large range of changes of the angle of attack does not change its position.
- BMoves forward.
- CMoves aft.
- DDoes not change its position in the full range of changes the angle of attack.
193Środek parcia to punkt: Center of Pressure (CP) is a point:
- AW 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.
- BWzględem 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).
- CRównoodległy od noska i ostrza (spływu) profilu. At the same distance from the leading edge and the trailing edge of profile.
- DKtóry 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.
194Change suppression of flight parameters has an affect:
- ADynamic stability.
- BStatic stability.
- CIncreased static stability.
- DNeutral static stability.
195 Buffeting of the tail surfaces is otherwise known as:
- ABuffeting.
- BPre-stall buffet.
- CAilerons flutter.
- DTail flutter.
196Ujemny skos skrzydła powoduje: The negative slant of wing causes:
- AZmniejszenie stateczności statycznej podłużnej. Reduction in the longitudinal static stability.
- BZwiększenie stateczności statycznej podłużnej. Increase of the longitudinal static stability.
- CZmniejszenie 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.
- DZwiększenie 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.
197Usterzenie kierunku zaprojektowane jest w celu obracania płatowca względem: Tail of the direction designed to rotate the airframe towards:
- Aośi OZ›. Z- yaw axis.
- Bośi OX›. X- roll axis.
- Cośi OY›. Y- lateral axis.
- Dośi OX› i ośi OY›. X- roll axis and the y lateral axis.
198Usterzenie wysokości zaprojektowane jest w celu obracania płatowca względem: Tail height designed to rotate the airframe towards:
- Aośi OY›. Y- lateral axis.
- Bośi OZ›. Z- yaw axis.
- Cośi OX›. X- roll axis.
- Dośi OZ› i ośi OX›. Z- yaw axis and the x roll axis.
199W celu zlikwidowania momentu oporowego lotek z reguły stosuje się: To eliminate of the aileron torque resistance as principle we use:
- ARóżnicowe wychylenie lotek. Lift augmentation system differential aileron deflection.
- BDodatkowe wychylenia klapo-lotek. Extra-aileron deflection flap- aileron.
- CWychylenie lotek o dokładnie ten sam kąt. Aileron deflection by exactly the same angle.
- DJak najmniejsze wychylenia lotek. The lowest aileron deflection.
200W codziennym życiu spotykamy się ze stanem równowagi: In everyday life we meet the state of stability:
- A- stałej ; - obojętnej; - chwiejnej - fixed -neutral- unstable
- B- stałej ; - chwiejnej; - ruchomej - fixed -unstable- mobile
- C- stałej ; - obojętnej; - ruchomej - fixed- neutral- mobile
- D- nieobojętnej; - obojętnej; - chwiejnej -indifferent- indifferent- unstable
Información
- Descripción
- Quiz on Principles Of Flight, created by Roman Eidia on 30/09/2018.
- Autor
- Roman Eidia
- Idioma
- English
- Visitas
- 90
- Etiquetas
- Valoración
- Aún sin valoraciones Valora este test