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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Sprache

Englisch

Kategorie

Technik

Stufe

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Erstellt / Aktualisiert

28.04.2022 / 11.05.2022

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What is the name of the graph showing the dependence between coefficients of lift CL and drag CD of the aircraft?

The Drag Polar.

Polar speed curve.

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.

Does not change.

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

t = 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.

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.

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