PL080 - Principles of Flight PPL(A)

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This flashcard set delves into the principles of flight for private pilots, covering key concepts like aerodynamics, aircraft stability, and control. It explores how factors such as angle of attack, air pressure, and wing design influence flight dynamics, including speed, drag, and lift. The set is particularly useful for aspiring pilots and aviation enthusiasts seeking to understand the fundamental physics behind aircraft maneuverability and performance.

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370

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English

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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.

Absolute stability.

Absolute instability.

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

Absolute instability.

Neutral stability.

Dynamic stability.

Absolute stability.

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:

Increases 4 times.

Increases 2 times.

Decreases 4 times.

If you double the velocity, the drag force:

Increases 4 times.

Increases 2 times.

Decreases 4 times.

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.

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.

Which axis is called normal axis?

OZ-axis?

OX-axis?

Axis OY?

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 OY?

OZ-axis?

Axis OX?

Such names are not used.

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 Mean Camber line.

The line connecting the most rear points of aerofoil is:

Trailing edge.

Leading edge.

The chord line.

The Mean Camber line.

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

The Mean Camber line.

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.

"Frise" ailerons-type are used to:

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.

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PL080 - Principles of Flight PPL(A)

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