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1st_MIDTERM > AERODYNAMICS > Flashcards

AERODYNAMICS Flashcards

1
Q

When a fluid is in motion, it must move
in such a way that mass is conserved.

A

CONTINUITY EQUATION

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2
Q

As long as the flow is steady, the mass
that flows through the cross-section at
point 1 must be the same as the mass
that flows through the cross section at
point 2

A

CONTINUITY EQUATION

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3
Q

Sound waves travel through the air at a
definite speed.

A

SPEED OF SOUND

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4
Q

This is obvious from natural observation;

A

SPEED OF SOUND

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5
Q

The ____________ in a perfect gas
depends only on the temperature of the
gas.

A

SPEED OF SOUND

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6
Q

It is a function of the temperature.

A

SPEED OF SOUND

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7
Q

It is the flow velocity divided by the speed of sound.

A

MACH NUMBER

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8
Q

Mach number Named after ____________.

A

ERNST MACH

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9
Q

FLOW IN WHICH THE DENSITY OF THE
FLUID ELEMENTS CAN CHANGE FROM
POINT TO POINT.

A

COMPRESSIBLE FLOW

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10
Q

MEANING THE DENSITY AT POINT 1 IS
NOT EQUAL TO THE DENSITY AT POINT
2.

A

COMPRESSIBLE FLOW

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11
Q

STRICTLY SPEAKING, ALL REAL-LIFE
FLOWS ARE COMPRESSIBLE. THERE
ARE CASES WHERE THE DENSITY
CHANGES ONLY SLIGHTLY

A

COMPRESSIBLE FLOW

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12
Q

FLOW IN WHICH THE DENSITY OF THE
FLUID ELEMENTS IS ALWAYS CONSTANT.

A

INCOMPRESSIBLE FLOW

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13
Q

HOWEVER, FOR THOSE FLOWS IN
WHICH THE CHANGE IN DENSITY IS
SMALL, IT IS CONVENIENT TO ASSUME
THAT ρ (RHO) IS CONSTANT.

A

INCOMPRESSIBLE FLOW

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14
Q

IT MEANS DENSITY IS CONSTANT ALONG THE FLOW.

A

INCOMPRESSIBLE

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15
Q

IT MEANS DENSITY IS NOT CONSTANT ALONG THE FLOW.

A

COMPRESSIBLE

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16
Q

THIS EQUATION STATES THAT AN
INCREASE IN VELOCITY LEADS TO AN
DECREASE IN PRESSURE.

A

BERNOULLI’S EQUATION

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17
Q

THE HIGHER THE VELOCITY OF THE FLOW, THE LOWER THE PRESSURE.

A

BERNOULLI’S EQUATION

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18
Q

IT IS THE LOWERING OF FLUID PRESSURE IN
REGIONS WHERE THE FLOW VELOCITY IS INCREASED.

A

BERNOULLI EFFECT

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19
Q

They are large tubes with air moving inside.

A

WIND TUNNELS

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20
Q

They are used to copy the actions of an object in flight.

A

TUNNELS

21
Q

They use wind tunnels to learn more about how an aircraft will fly.

A

RESEARCHERS

22
Q

It is a device for testing aircraft and its components in a controlled airstream under
laboratory conditions.

A

WIND TUNNELS

23
Q

They put a model of an airplane in the tunnel and then study the way air moves around the model.

A

SCIENTISTS AND ENGINEERS

24
Q

They are usually made out of steel or aluminum, that are tested and loaded with many instruments and sensors that report back to the computers in the control room.

A

WIND TUNNELS

25
Q

They use wind tunnels to test models of proposed aircraft.

A

AERODYNAMICISTS

26
Q

They are used for operations at very low Mach Number, with speeds in the test section up to 400 km/h

A

LOW-SPEED WIND TUNNELS

27
Q

These types of Wind tunnels are able to
achieve speeds close to the speed of sound.
The highest speed is reached in the test
section.

A

TRANSONIC WIND TUNNELS

28
Q

It should produce supersonic speeds (Mach numbers up to 5)

A

SUPERSONIC WIND TUNNELS

29
Q

It achieved with an appropriate design of a
convergent-divergent nozzle.

A

SUPERSONIC WIND TUNNELS

30
Q

It is designed to generate a hypersonic flow field in the working section.

A

HYPERSONIC WIND TUNNELS

31
Q

The speed of these tunnels varies from Mach 5 to 15.

A

HYPERSONIC WIND TUNNELS

32
Q

These types of tunnels must run intermittently
with very high-pressure ratios when initializing.

A

HYPERSONIC WIND TUNNELS

33
Q

In subsonic wind tunnels, a convenient way of measuring the pressure difference (P1-P2) is by means of _______________.

A

MANOMETER

34
Q

It is a measure of the purely random motion of molecules in the gas.

A

STATIC PRESSURE

35
Q

It is due simply to the random motion of the molecules.

A

STATIC PRESSURE

36
Q

It can also be the pressure of the air around the aircraft at a certain point.

A

STATIC PRESSURE

37
Q

It is related to the velocity of the air.

A

DYNAMIC PRESSURE

38
Q

It represents the kinetic energy per unit volume of a fluid due to its motion.

A

DYNAMIC PRESSURE

39
Q

It is the measure of the impact pressure or “ram air” pressure caused by the forward motion
of the aircraft through the air.

A

DYNAMIC PRESSURE

40
Q

It is the sum of the free-stream dynamic pressure and free-stream static pressure.

A

TOTAL PRESSURE

41
Q

At a ___________, the fluid velocity
is zero.

A

STAGNATION POINT

42
Q

In the case where the fluid is not
moving, _____________ is also the same
as the static pressure.

A

TOTAL PRESSURE

43
Q

The pitot tube was invented by a
Frenchman, named _______________.

A

HENRI PITOT

44
Q

It is an instrument that measures the
total pressure at a point in the flow.

A

PITOT TUBE

45
Q

It is most often a flush-mounted hole on the fuselage of an aircraft.

A

STATIC PORTS

46
Q

It is obtained through a static port.

A

STATIC PRESSURE

47
Q

It is a system of pressure-sensitive instruments that is most often used in aviation.

A

PITOT-STATIC SYSTEM

48
Q

It consists of a pitot tube, a static port,
and the pitot-static instruments.

A

PITOT-STATIC SYSTEM

1st_MIDTERM (3 decks)

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