Are cambered aerofoils much more "sensitive" to contamination than laminar profiles?
No.
Yes.
No, but only for small angles of attack.
Yes, but only at high angles of attack.
To prevent airleron flutter it is necessary to:
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.
To prevent bending-torsional flutter it is necessary to:
Increase the torsional rigidity of the wing and move the wing CoG closest to the axis of torsion.
To prevent airleron reversal it is necessary to:
Increase the torsional rigidity of the wing.
Apply aerodynamic ballance.
Apply balance tab.
Apply anti-balance tab.
To prevent buffeting it is necessary to:
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.
An aerodynamic leading edge is a line joining the points of airfoil where:
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.
Lack of airlerons mass balance during high-speed flight is a direct cause of:
Aileron flutter.
Bending- torsional flutter.
Airleron reversal.
Wing torsional divergence.
Buffeting means:
Shaking of control surfaces.
Bending- torsional vibrations.
Aileron flatter.
Tailplane flatter.
An object moves with the speed V on a circular track. A double increase of the object's speed will cause the following:
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.
An object moves with the speed V on a circular track. A double increase of the track's radius will cause the following:
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.
An object moves with the speed "V" on a circular track with radius "R". The resultant acceleration vector is always directed:
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.
Static pressure at the separation point (change from laminar flow to turbulent flow) is:
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.
What does "the universal gas law" mean?
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
What dose the term " controllability " of a flying object ( plane, helicopter, glider, hang-glider etc) mean?
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.
What does "stagnation pressure" mean?
The difference between the dynamic and static pressure.
The highest measured pressure.
The lowest measured pressure.
The sum of a dynamic and static pressure.
What is a "laminar flow"?
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.
What does the aircraft (helicopter, glider, etc.) "absolute ceiling" mean?
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.
What does "static stability" of an object mean? (aircraft, helicopter, grinder, hang-grinder etc.)
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.
What does "airfoil Center of Pressure" mean?
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.
What does the boundary layer mean"
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.
What is an "Aspect Ratio" of an aircraft or glider wing (or a propeller blade)?
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.
What is the elevation of the airport?
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.
What is the air density?
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.
What is this the International Standard Atmosphere (ISA)?
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.
What is it a pressure altitude above the airport level?
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.
What is pressure altitude above sea level?
A reading of a pressure altimeter when it is set to the current sea level pressure QNH.
A reading of a pressure altimeter when it is set to the current airport pressure QFE.
What is density altitude?
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.
What is the standard height?
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.
Density altitude, corrected for ambient temperature.
Is there any connection between air static pressure (p), the absolute temperature (T) and density (rho)?
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.
Does the object (aircraft, helicopter, glider, hang-glider, etc.) statically unstable can be dynamically stable?
Static stability is not important for the dynamic stability.
Fixed-wing aircraft - yes, Rotorcraft - no.
Does increase of stability affect controlability?
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.
What is the difference between static stability and dynamic stability of an object (airplane, helicopter, glider, hang-glider etc.)?
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.
What is the "static instability" of an object (airplane, helicopter, glider, hang-glider etc.)?
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.
What is the "neutral static stability" of an object (airplane, helicopter, glider, hang-glider etc.)?
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.
What kind of profile doesn't create induced drag at zero angle of attack?
Double convex symmetrical.
Plano-convex.
Concave-convex.
Double convex asymmetrical.
For a constant accelerated motion, double increase of time at a constant acceleration causes:
A fourfold increase of the distance.
A double increase of the distance.
A double reduction of the distance.
A fourfold reduction of the distance.
For a constant accelerated motion, double increase of acceleration within a constant time causes:
A double increase in the distance.
A fourfold increase in the distance.
A double reduction in the distance.
A fourfold reduction in the distance.
For a rectangular planform wing it is true that:
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.
For the three wings with the same surface and the same wingspan, but with different planform (rectangular, tapered and elliptical), the Aspect Ratio is:
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.
For an established descent the following equation is true:
Px=Q
Pz=Q
Q=Q
Pz=Px
What is the "drag polar"?
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.
The wing surface increasing devices are:
Fowler flap and the leading edge flaps.
Winglets and trailing edge flaps.
Slots and the split flaps.
Trainling edge flaps and the split flaps.
Devices that move the separation point aft on an airfoil upper surface are called:
Slats.
Trailing edge flaps.
Split flaps.
Fowler flap.
Devices that increace the camber of an airfoil are called:
Leading edge flaps.
Winglets.
Slots.
All answers are correct.
The backward sweep of a wing causes:
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.
Aaerofoil glide ratio:
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.
Doubling an airflow velocity in a closed tunnel will result in:
A fourfold decrease of static pressure.
A fourfold increase of static pressure.
A twofold increase of static pressure.
A double decrease of static pressure.
Flatter is the name of a phenomenon associated with:
The occurrence of self-existing vibrations.
The formation of the lift force.
The formation of drag force.
Elevator/rudder/aileron reversal.
When air enters a channel with velocity "V" and the channel cross-sectional area changes, that velocity also changes:
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.
Aerofoil thickness is:
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.
Im większa lepkość powietrza tym: The greatest distance between. The bigger air viscosity:
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.
The existence of steerring control surfaces on the airframe causes mainly:
Additional drag caused by slots between those surfaces and wings.
Induced drag.
Wave drag.
Skin friction drag.
What is a "flettner"?
Balance tab.
Anti-balance tab.
Trim tab.
Trimmer .
How does the speed have to change in a balanced turn in order to increase the radious four times (keeping the same bank angle)?
Double.
Increase 4 times.
Increase 8 times.
Reduce 4 times.
What is the name of a tab, which position may be independently changed during the flight?
Flettner.
What is the name of the point at which the airflow changes from laminar to turbulent?
Separation Point.
Stagnation Point.
Pressure Point.
Turbulent point.
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?
Biegunowa. The Drag Polar.
Krzywa doskonałości. Airfoil fineness curve.
Biegunowa prędkości. Polar speed curve.
Wykres sprawności. Chart performance.
What is the aircraft's VNE?
Never Exceed Speed.
Cruising speed.
Economic speed.
Optimal speed.
What are the SI units and symbols of mass, length and time?
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).
What are the SI units and symbols of force, pressure and temperature?
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).
What is the pressure of 1000 hPa in SI basic units?
100000 N/m.
1000000 N/m.
1000 N/m.
10000 N/m.
How will the radius of a balanced turn change if the speed doubles at the constant bank angle?
Increases 4 times.
Increases 2 times.
Increases 8 times.
Does not change.
How does the density altitude change when the air temperature is higher than ISA ?
Increases.
Slightly decreases.
Decreases inversly proportional to the relative density sigma.
What is the difference between flat and steep spin?
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.
What is the standard ISA air pressure at sea level expressed in mmHg (corresponds to po = 1013.25 hPa)?
760 mm Hg.
800 mm Hg.
750 mm Hg.
860 mm Hg.
What is the name of a ratio of static pressure at any height to the standard ISA pressure at sea level - delta = p/po?
Relative pressure.
Standard pressure.
Modulal pressure.
The Hypocrite's Number.
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?
The relative air density.
Laplace's constant.
The M/S ratio.
The Piccard's ratio.
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?
The dimensionless relative temperature.
The absolute temperature.
The Don Pedro's constant.
The d'Amore coefficient.
What is the reference (standard) static pressure at sea level?
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.
What is the reference (standard) air temperature at sea level expressed in Kelvins (K)?
To = 288 K.
To = 258 K.
To = 277 K.
To = 301 K.
What is the reference (standard) air density at sea level expressed in kg/m2?
rho o = 1.2255 kg/m2.
rho o = 1.0000 kg/m2.
rho o = 1.0255 kg/m2.
rho o = 1.2000 kg/m2.
What is the reference (standard) air temperature at sea level expressed in degrees Celsius (deg. C) ?
t = 15 deg. C
t = 10 deg. C
t = 20 deg. C
16.5 deg. C
What relationship exists between the air temperature t expressed in degrees Celsius (deg. C) and temperature T expressed in Kelvins (K)?
T = t + 273.
T = t + 233.
T = t + 283.
T = t + 373.
What are the main features of a thick profile compared to a thinner one at the same velocity of an airflow?
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.
What are the parameters used to describe the physical condition of the air?
Static pressure, temperature and density.
Humidity and dynamic pressure.
Temperature, density and kinematic viscosity.
The content proportions of nitrogen and oxygen.
What are the prefixes of the SI units that mean the multiplication by 10, 100 and 1000?
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).
What data is needed to calculate the load factor "n" in a balanced turn?
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.
What is purpose of "lift ugmentation systems" (flaps, slats, spoilers, etc.)?
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.
What is the name of the instrument that measures the actual height or distance of an aircraft from the ground?
The Radio altimeter (radar).
The pressure altimeter.
The optical rangefinder.
The DME.
One of the measurement of dynamic stability of an object (airplane, helicopter, glider, hang-glider, etc.) is so called "half-time". What is it?
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.
If the body displaced from an equilibrium by a short-term external force is moving with constant spedd, then that body exhibits:
Neutral stability.
Dynamic stability.
If the body displaced from an equilibrium by a short-term external force is in constant accelerated motion, then that body exhibits:
Absolute instability
If we add separate drags of all parts of the airframe (eg. wings, fuselage, tail, etc.), then the obtained sum is:
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.
If you double the velocity, the lift force:
Decreases 4 times.
Decreases 2 times.
If you double the velocity, the drag force:
If you reduce the temperature of the airflow, without changing the angle of attack, wing area and flow rate then:
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.
If we increase the surface of the horizontal stabilizer:
Longitudinal static stability increases.
Longitudinal static stability decreases.
Longitudinal controllability increases.
Longitudinal controllability does not change.
Każde ciało ma swój własny, stały i niezmienny współczynnik oporu kształtu Cx kszt:
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.
The angle of attack for which Cd is minimum is always:
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.
Angle of attack of the airfoil profile which is concave-convex shaped, for which there is no induced drag created has the value:
Negative.
Positive.
Zero
Critical.
Angle of attack of profile is the angle between:
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.
Angle between the chord line and the direction of undisturbed airflow is:
Profile angle of attack.
Profile convergence angle.
Dihedral angle.
Sweepback angle.
When altitude indicated on the ground by the pressure altimeter is a pressure altitude equal to the elevation of the airport?
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.
Flaps are used to:
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.
Compensation aerodynamic rudder is designed to:
Reduce control forces.
Balance the control surface in neutral position.
It act as mass balance of control surface.
Increase control forces.
Aerodynamic compensation of rudder is also called aerodynamic balance of the rudder.
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.
Flat spin is:
More dangerous than the steep.
Slightly less dangerous than the steep.
Same dangerous as the steep spin.
A lot less dangerous than the steep.
Critical flutter speed is the speed for which:
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.
Którą oś układu współrzędnych nazywamy osią pionową? Which axis is called normal axis?
Oś OZ? OZ-axis?
Oś OX? OX-axis?
Oś OY? Axis OY?
Takiej nazwy nie używa się. Such names are not used.
Which axis of the coordinate system is called the longitudinal axis?
OX-axis?
Axis OY?
OZ-axis?
Such names are not used.
Which axis is called the lateral axis?
Axis OX?
Which devices are not lift augmentation wing devices?
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.
What is a potential energy?
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].
The curve representing the shape of wings as seen from above is:
The planform of the wing.
The outline of the profile.
The Mean Camber line.
The Mean Chord line.
The line connecting the most front points of aerofoil is:
Leading edge.
Trailing edge.
The chord line.
The line connecting the most rear points of aerofoil is:
The line drawn equidistant between the upper and lower surfaces of an aerofoil is called:
The Chord line.
Maximum Camber.
Maximum Thickness.
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:
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.
"Frise" ailerons-type are used to:
Neutralize adverse yaw.
Increase banking momentum.
Reduce skin friction drag.
Reduce form drag during aileron deflection.
OX axis.
OY axis.
OZ axis.
OZ axis and OY axis.
The never exceed speed "VNE"is:
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.
Maximum effeciency of profile:
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.
The maximum speed of flight in turbulent air is:
VRA.
VNE.
VNO.
VA.
The maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load is determined as:
Lift augmentation is used to:
Reduce drag force at low speeds.
Improve the stability of the full range of angles of attack.
The minimum value of Cx coefficient we can obtain for the angle of attack equal 0°.
Is true only for symmetric profiles.
Always true.
Is always false.
True but only for asymmetrical profiles.
Aerodynamic momentum measured from the aerodynamic center in flight speed range:
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.
Aileron adverse yaw is because:
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.
On the lower surface of the wing air flow is deflected towards wing tip:
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.
On the upper surface of the wing air flow is deflected towards wing root:
The greater angle when the angle of attack is greater.
The smaller angle when the angle of attack is greater.
At what altitude, density of the air in ISA atmosphere is equal to one-fourth of the ISA density at sea level?
12200 m.
11000 m.
10000 m.
13330 m.
At what altitude, density of the air in ISA atmosphere is equal to the ISA density at sea level?
0 m.
100m.
105m
17,5 m.
At what altitude, density of the air in ISA atmosphere is equal to half of the ISA density at sea level?
FL180
FL250
FL100
FL050
On what altitude pressure is equal to half of pressure at sea level in ISA atmosphere?
FL180.
FL250.
FL100.
FL050.
Air flow around the wing is deflected towards:
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.
The maximum distance between the upper and lower surfaces of the aerofoil is:
Height of profile.
Thickness Chord Ratio.
Profile height ratio.
The highest speed at which you can fly in calm air is:
Momentum relative to normal, which arises from the aileron deflection by the same angle in opposite directions is called:
Adverse yaw.
Roll momentum.
Dutch roll.
Aileron hinge moment.
Niestateczność holendrowania to jeden z rodzajów niestateczności: Dutch roll is one of the types of instability:
Dynamicznej bocznej. Directional dynamic.
Statycznej kierunkowej. Directional static.
Dynamicznej poprzecznej. Lateral dynamic.
Dynamicznej kierunkowej. Lateral static.
Niestateczność spiralna to jeden z rodzajów niestateczności: Spiral instability is one of types of instability:
Dynamicznej bocznej. Lateral dynamic.
Statycznej podłużnej. Directional static.
Dynamicznej poprzecznej. Directional dynamic.
Slightly increase of the angle of attack in range just below maximum angle of attack causes:
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".
Wing icing causes:
Increase of the minimum speed.
Increase of the lift force.
Decrease of the rate of descent.
Decrease of the drag.
Airframe rotation around OX axis is realized through:
Aileron.
Elevator.
Rudder.
Flaps.
Airframe rotation around OY axis is realized through:
Ailerons.
Airframe rotation around OZ axis is realized through:
Opór ciała poruszającego się w powietrzu zależy od: Induced drag increases when:
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.
Opór indukowany wzrasta, gdy: Induced drag increases when:
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.
Interference drag is caused by:
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.
Form drag depends only on the shape of the body:
False, form drag also depends on the body position in airflow.
False, form drag does not depend on the shape of the body
Is true only for the airfoil.
Aerofoil skin friction drag in cruise flight angles of attack is the smallest when the airflow is:
Laminar.
Turbulent.
Spanwise.
Lilienthal.
Skin friction drag of laminar airflow compared to turbulent air flow is:
Lower.
Is always higher.
The same for a perfectly clean surface, in other cases higher.
Always the same.
Drag which is due to vortices at wing tips caused by equalizing air pressure on the upper and lower surfaces is called:
Interference drag.
Wave resistance.
Rotational drag.
All-moving tailplane is a horizontal stabilizer and elevator:
True, but only if the airframe is statically unstable.
True, but only if the airframe is dynamically unstable.
What will happen after exceeding speed which is limited by wing torsional rigidity:
Wings will twist (critical damage).
Flutter.
Buffeting.
Ailerons reversal.
After aileron deflection at high speed arise:
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.
During spin entry, the wing, which has higher angle of attack:
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.
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:
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.
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:
Jest stałe. Is constant.
Poszerzacze stosuje się w celu: Fowler flaps are used to:
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.
Powierzchnia nośna skrzydła to: Wing area which generates lift is:
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.
The reson of skid in turn can be:
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.
The reson of slip in turn can be:
Too high bank angle or too small angular velocity
Design manoeuvering speed "Va" is:
The maximum speed at which you can still use the full controls deflection without exceeding the maximum airframe load.
The maximum flight speed in calm air.
The speed to which all kinds of manoeuvres are permitted.
Speed for rough air operations, VRA is:
Laminar aerofoil are those of which:
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.
Prosta łącząca środek krzywizny noska profilu z ostrzem (spływem) profilu to: The straight line joining leading and trailing edge of the wing aerofoil is:
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.
Dynamic stall differs from the static because during the dynamic stall:
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.
Static stall is characterized by
A slow change of angle of attack of the wing.
A rapid change of angle of attack of the wing.
An increase in static stability.
Airflow around the wing tips due to equalizing pressure on the upper and lower surfaces creates vortices, which:
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.
Forward movement of Center of gravity:
Decreases possibility of a flat spin entry.
Increases possibility of a flat spin entry.
Facilitates spin entry.
Makes recovery from a spin more difficult.
Aft movement of Center of gravity:
Makes spin entry more difficult.
Facilitates spin recovery.
With increasing angle of incidence of the wings:
Increases the difference of lift produced on both wings during the slip.
Lateral controlability is increasing.
Lateral static stability decreases.
Minimum speed decreases.
With increasing bank angle in coordinated turn G-force:
Decreases.
Gforce does not depend on bank angle, but on the airspeed.
Przyczyną zjawiska trzepotania usterzeń jest wystąpienie: The cause of buffeting is:
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.
Increase of lift force on the elevator caused by the movement of yoke or stick is:
Positive if we move yoke forward.
Negative if we move yoke forward.
Is always positive.
Is always negative.
The point on aerofoil, which is locatede the most aft to the direction of flight is:
Back edge.
Front edge.
The point on aerofoil, which is located the most forward to the direction of flight is:
Arrow.
The point, where the line of resultant aerodynamic force intersects the chord line is:
Centre of Pressure.
Aerodynamic center.
Profile center.
Geometric center.
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:
Geometric centre.
The difference of increase of drag forces resulting from the aileron deflection by the same angle but in opposite directions gives:
A favorable deflection.
Adverse roll.
A favorable yaw.
Differential aileron deflection is used to:
Increase roll moment.
Reduce aileron hinge moment.
Reduce forces necessary for aileron deflection.
The movement of the aircraft during flight is described by:
Three axes OX, OY, OZ.
Two axes OX and OY.
One axis OX.
Four axes OW, OX, OY, OZ.
Drag force of the wing moving down in the spin entry phase is:
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.
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:
Siła oporu kształtu.Form drag.
Siła oporu tarcia. Skin friction drag.
Siła oporu indukowanego. Induced drag.
Siła oporu interferencyjnego. Interference drag.
Aerodynamic forces depend on the air density. How do they change when the density decreases?
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.
Slats are used to:
Vertical stabilizer is primarily responsible for stability:
Directional.
Longitudinal.
Lateral.
Vertical.
Horizontal stabilizer is primarily responsible for following stability:
Horizontal.
Stateczność dynamiczna boczna dotyczy: Dynamic lateral stability concerns:
Odchylania i przechylania. Rolling and yawing.
Tylko pochylania. Only pitching.
Tylko przechylania. Only rolling.
Tylko odchylania. Only tilting.
Stateczność dynamiczna podłużna dotyczy: Longitudinal dynamic stability concerns:
Pochylania. Pitching.
Przechylania.Rolling.
Odchylania. Yawing.
Odchylania i przechylania. Yawing and rolling.
Stateczność dynamiczną boczną można nazwać inaczej: Dutch roll concerns:
Statecznością holendrowania. Directional and lateral stability.
Statecznością kierunkową. Directional stability.
Statecznością poprzeczną. Lateral stability.
Statecznością dynamiczną podłużną. Longitudinal dynamic stability.
Stateczność statyczna kierunkowa dotyczy: Static directional stability concerns:
Przechylania. Rolling.
Stateczność statyczna podłużna dotyczy: Static longitudinal stability concerns:
Stateczność statyczna poprzeczna dotyczy: Static Lateral Stability of concerns:
The ratio of the distance traveled in that time is:
The average speed.
The average acceleration.
Instantaneous velocity.
Instantaneous acceleration.
The ratio of the surface of the wing span is:
The Mean Geometric Chord.
Aspect ratio.
Convergence.
The Angle of Sweepback.
Change of the velocity at time t to time t is:
Distance traveled by the body at time t.
Change in kinetic energy of the body.
Strzałka profilu to: Maximum Thickness:
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.
Szkieletowa profilu to: The Mean Camber Line:
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.
The average angular acceleration in a rotating movement is:
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.
The aerodynamic center is the 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).
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.
The aerodynamic center wiith the increase of angle of attack:
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.
Środek parcia to punkt: Center of Pressure (CP) is a point:
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.
Change suppression of flight parameters has an affect:
Static stability.
Increased static stability.
Neutral static stability.
Buffeting of the tail surfaces is otherwise known as:
Pre-stall buffet.
Ailerons flutter.
Tail flutter.
Ujemny skos skrzydła powoduje: The negative slant of wing causes:
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.
Usterzenie kierunku zaprojektowane jest w celu obracania płatowca względem: Tail of the direction designed to rotate the airframe towards:
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.
Usterzenie wysokości zaprojektowane jest w celu obracania płatowca względem: Tail height designed to rotate the airframe towards:
ośi OZ› i ośi OX›. Z- yaw axis and the x roll axis.
W celu zlikwidowania momentu oporowego lotek z reguły stosuje się: To eliminate of the aileron torque resistance as principle we use:
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.
W codziennym życiu spotykamy się ze stanem równowagi: In everyday life we meet the state of stability:
- stałej ; - obojętnej; - chwiejnej - fixed -neutral- unstable
- stałej ; - chwiejnej; - ruchomej - fixed -unstable- mobile
- stałej ; - obojętnej; - ruchomej - fixed- neutral- mobile
- nieobojętnej; - obojętnej; - chwiejnej -indifferent- indifferent- unstable
