The EASA
ATPL Principles of Flight
test bank contains questions pertaining to
081-01-01 Basics, laws and definitions
. The following list contains only a relatively small percentage of the pertinent
questions. Our software, which you are free to download now at no cost, will
generally contain a much more complete set of questions associated with this
test bank. This list is intended only to familiarize you in a general way with
the questions of the
Principles of Flight
test bank.
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Principles of Flight
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That said, while the following questions are intended
as a general familiarization tool, this list may not be up-to-date nor accurate.
We do not update this website as often as we update our software, which will
contain at any moment all questions that we have for a given test / topic. Therefore,
if you need to actually study for your test, instead of using the list below,
we strongly, strongly encourage you to download our GroundSchool
EASA ATPL
Written Test Prep Software and Apps. Not only is it more complete and up-to-date, but is also considerably faster and more efficient as a study tool.
| Sample Questions
from the EASA ATPL
Principles of Flight
Test Bank |
- the density change in the flow is less than:
- How is the thickness of an aerofoil section measured?
- What is the SI unit that results from multiplying kg and m/s2?
- The load factor n is:
- Which of the following statements, about a venturi in a sub-sonic airflow are correct?the dynamic pressure in the undisturbed flow and in the throat are equal.the total pressure in the undisturbed flow and in the throat are equal.
- Considering a positive cambered aerofoil, the pitch moment when Cl=0 is:
- Where does the lift act on the wing?
- An A 310 aeroplane weighing 100 tons is turning at FL 350 at constant altitude with a bank of 50 degrees. Its flight Mach range between low-speed buffering and high-speed buffering goes from:
- Compared to a wing at sea level at 200kt TAS, a wing at 40,000ft at 400kt TAS and the same angle of attack will have:
- The Principle of Continuity states that in a Stream tube of decreasing cross-sectional area, the speed of a subsonic and incompressible airflow will:
- The following unit of measurement kgm/s2 is expressed in the SI-system as:
- The SI unit of energy is:
- What is the CL and CD ratio at normal angles of attack?
- The resistance, or skin friction, due to the viscosity of the air as it passes along the surface of the wing is part of the:
- In straight and level flight the center of pressure is behind the center of gravity. With the resultant force from the elevators and tailplane action to maintain straight and level flight, the force would be action:
- Which of the following expressions is correct (F=force; m=mass, a=acceleration):
- An aircraft is flying at sea level with an indicated airspeed of 210kts. What will be the true airspeed at that time?
- Load factor is the actual lift supported by the wings at any given time:
- The formula for lift is:
- Which of the following wing planform gives the highest local profile lift coefficient at the wing root?
- Longitudinal dihedral is:
- Maintaining thickness/chord ratio but changing to a supercritical wing section will:
- Dihedral of the wing is:
- The angle of attack of a two dimensional wing section is the angle between:
- The chord line is:
- What happens to total drag when accelerating from CL MAX to maximum speed?
- If you want to maintain a constant TAS during a climb, you should during the climb:
- Flying at the maximum rate of climb speed (Vy) you will obtain maximum:
- A laminar boundary layer is a layer, in which:
- For an aircraft in level flight, if the wing center of pressure is aft of the center of gravity and there is no thrust/drag couple, the tailplane load must be:
- When does P-factor cause the airplane to yaw to the left?
- The movement of an aircraft is defined along three axes which all pass through:
- Wing loading is:
- Consider a certain stream line tube. The velocity of the stream in the tube is V. An increase of temperature of the stream at constant value of V will:
- Bernoulli’ s Theorem states:
- Dynamic pressure is expressed as:
- A symmetrical aerofoil section at CL = 0 will produce?
- The airfoil chord line is:
The
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access to all available questions. |
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more information about the EASA ATPL
Principles of Flight
test bank, click here.
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