Bernouli's Principal Flashcards

1
Q

Bernoulli’s principal is best described using
which effect?
a. Coriolis effect.
b. Venturi effect.
c. Neither a nor b

A

b. Venturi effect.

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2
Q

Concerning the Venturi effect, as the crosssectional area of a tube is reduced, the
velocity of the airflow through the tube
must–
a. Decrease
b. Increase
c. Remain the same

A

b. Increase

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3
Q

As the velocity of the air moving through a
venturi increases–
a. Static pressure decreases
b. Static pressure increses
c. Static pressure is difficult to measure and therefore an increase or decrease is considered neglible

A

a. Static pressure decreases

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4
Q

Static pressure is defined as–
a. Compressed air containing positively
charged ions.
b. The atmospheric pressure of the air through which an airplane is flying.
c. The pressure

A

b. The atmospheric pressure of the air through which an airplane is flying.

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5
Q

Dynamic pressure is defined as–
a. Compressed air containing positively
charged ions.
b. The atmospheric pressure of the air through which the airplane is moving.
c. The pressure of a fluid resulting from its motion.
d. None of the above.

A

c. The pressure of a fluid resulting from its motion.

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6
Q

Relative wind is–
a. The air in motion that is equal and opposite the flight path velocity of the airfoil.
b. The angle measured between the resultant relative wind and the chord.
c. The angle between the airfoil chord line and
the longitudinal axis of the airplane.
d. None of the above.

A

a. The air in motion that is equal and opposite the flight path velocity of the airfoil.

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7
Q

Angle of Attack is the angle measured between the resultant relative wind and the chord
a. True
b. False

A

a. True

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8
Q

Center of Pressure is defined as:
a. The point along the mean camber line where all aerodynamic forces are considered to act.
b. The point along the chord line of an airfoil through which lift is considered to act.
c. The point along the chord line on an airfoil through which all aerodynamic forces are considered to act.

A

c. The point along the chord line on an airfoil through which all aerodynamic forces are considered to act.

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9
Q

Aerodynamic center is the point along the chord line of an airfoil through which all aerodynamic forces are considered to act.
a. True
b. False

A

a. True

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10
Q

Lift is defined as–
a. the component of the total aerodynamic
force that acts at right angles to drag.
b. the component of the total aerodynamic force that acts at right angles to the RRW.
c. Neither a nor b are true.

A

b. the component of the total aerodynamic force that acts at right angles to the RRW.

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11
Q

The two factors that most affect the
coefficient of lift and the coefficient of drag
are:
a. weight & balance
b. thrust & air density
c. shape of the airfoil & angle of attack

A

c. shape of the airfoil & angle of attack

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12
Q

Drag that is produced by non-lifting
portions of the airframe.

a. Form Drag
b. Parasitic Friction Drag
c. Parasitic Drag

A

c. Parasitic Drag

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13
Q

The portion of drag that is generated because of the shape of the airplane.

a. Form Drag
b. Skin Friction Drag
c. Parasitic Form

A

a. Form Drag

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14
Q

The boundary layer air creates lstagnant layer of air molecules.

a. Parasitic Drag
b. Skin-Friction Drag
c. Interference Drag

A

b. Skin-Friction Drag

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15
Q

Created by the collision of airstreams. Causes eddy currents, restrictions, and turbulence to smooth flow.

a. Parasitic Drag
b. Skin-Friction Drag
c. Interference Drag

A

c. Interference Drag

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16
Q

Drag created as a result of the production of lift. Creates wingtip vortices and vertical velocities.

a. Parasitic Drag
b. Induced Drag
c. Interference Drag

A

b. Induced Drag

17
Q

Varies inversely with the airspeed.

a. Parasitic Drag
b. Skin-Friction Drag
c. Interference Drag

A

c. Interference Drag

18
Q

Total drag is that component of the total aerodynamic force parallel to the
___________ that tends to retard the motion
of the aircraft.
a. chord line
b. center of pressure
c. relative wind
d. none of the above

A

c. relative wind

19
Q

An airfoil with a higher lift to drag ratio is
more efficient than an airfoil with a lower
lift to drag ratio.
a. True
b. False

A

a. True

20
Q

A stall occurs when:
a. The airplane enters the region of reverse command.
b. The airplane is flown above CL max.
c. The airfoil is flown at an angle of attack greater than that for maximum lift.
d. None of the above.

A

c. The airfoil is flown at an angle of attack greater than that for maximum lift.

21
Q

An aerodynamic stall occurs when an increase in the angle of attack results in a loss of lift and is due to:
a. low airspeed
b. density altitude
c. seperation of boundary-layer air.

A

c. seperation of boundary-layer air.

22
Q

When the boundary layer separates, turbulence occurs between the boundary layer and the surface
of the wing. This results in–
a. an increase in dynamic pressure above the wing.
b. an increase in the static pressure above the wing.
c. Neither a or b

A

b. an increase in the static pressure above the wing.

23
Q

Increasing the AOA beyond the boundary-layer separation point will result in–
a. a further increase in lift.
b. the boundary-layer separation point moving forward on the airfoil.
c. a decreased top surface area of the wing available to produce
d. b & c

A

d. b & c

24
Q

Designing the wing to stall from the
wingtips progressively inboard toward the
root section is a desirable airplane design
characteristic.
a. True
b. False

A

b. False

25
Q

Define Geometric Twist–
a. A method used to counteract torque.
b. That stupid lemon they always ruin your Corona with.
c. The twist of an airfoil having different geometric angles of attack at different spanwise locations.

A

c. The twist of an airfoil having different geometric angles of attack at different spanwise locations.