Quiz about aerody

Question 1

It is determined by the altimeter and correlates to ambient pressure.

Accepted Answer

c. Pressure Altitude

Answer

a. Temperature Altitude

Answer

b. Density Altitude

Answer

d. None of the Above

Question 2

What are the three equations that will be used in deriving formulas to calculate for normal shock wave properties?

Accepted Answer

A. Mass, Momentum, & Energy Eq.

Answer

B. Momentum, Perfect Gas, & Continuity Eq.

Answer

C. Energy, Continuity, & Momentum Eq.

Answer

D. Perfect Gas, Equation of State, Momentum Eq.

Question 3

A shock wave that is unattached to the surface, staying ahead of the leading edge given specific conditions.

Accepted Answer

D. Bow Shock

Answer

A. Expansion Wave

Answer

B. Oblique Shock

Answer

C. Normal Shockwaves

Question 4

The sum of the energies of all the molecules in a finite volume of a gas.

Accepted Answer

B. Internal Energy

Answer

A. Enthalpy

Answer

C. Entropy

Answer

D. Perfect Gas

Question 5

In this flow, the density of the fluid is considered constant:

Accepted Answer

b. Incompressible flow

Answer

a. Compressible flow

Answer

c. Adiabatic flow

Answer

d. Isentropic flow

Question 6

This is the angle to which a flow can turn isentropically for a given initial and final Mach number. This is also the maximum angle through which a sonic flow can be turned around in a convex corner.

Accepted Answer

d. Prandtl Meyer Function

Answer

a. Mach Angle

Answer

b. Wave Angle

Answer

c. Prandtl Meyer Expansion Fan

Question 7

The specific heat ratio of a gas is 1.83. Assuming that the air is at standard condition, what is the cp and cv of the gas in English units?

Accepted Answer

b. 3783.47 ft. lb/slug.R and 2067.47 ft.lb/slug.R

Answer

a. 4783.47 ft. lb/slug.R and 3067.47 ft.lb/slug.R

Answer

c. 2783.47 ft. lb/slug.R and 3067.47 ft.lb/slug.R

Answer

d. 2067.47 ft. lb/slug.R and 3783.47 ft.lb/slug.R

Question 8

The ______ is the ratio of inertial forces to viscous forces within a fluid which is subjected to relative internal movement due to different fluid viscosities. It is also a dimensionless quantity that is used to determine the flow pattern while flowing through a pipe.

Accepted Answer

b. Reynolds Number

Answer

a. Mach Number

Answer

c. Specific Heat Ratio

Answer

d. Speed of Sound

Question 9

A Cessna 152 is flying with a velocity of 420 ft/s at a pressure altitude of 12000 ft. Given that the Mach number is 0.6, calculate for the density of air experienced by the aircraft.

Accepted Answer

C. 3.85 x 10-3 slug/ft3

Answer

A. 1.65 x 10-3 kg/m3

Answer

B. 5.24 x 10-3 kg/m3

Answer

D. 1.65 x 10-3 slug/ft3

Question 10

It is the rate at which the temperature in the atmosphere falls with altitude

Accepted Answer

d. Lapse rate

Answer

a. Temperature change rate

Answer

b. Enthalpy

Answer

c. Gradient rate

Question 11

Consider a normal shock wave where the upstream Mach number is 2. Compute for the downstream Mach number (k= 1.4).

Accepted Answer

b. 0.5774

Answer

a. 0.5092

Answer

c. 0.8544

Answer

d. 0.8321

Question 12

For a flow in a Subsonic Converging Nozzle, the:

Accepted Answer

b. Velocity increases; Pressure, Temperature, and Density decreases.

Answer

a. Velocity decreases; Pressure, Temperature, and Density increases.

Answer

c. Velocity and Temperature increases; Pressure and Density decreases.

Answer

d. Velocity and Temperature decreases; Pressure and Density increases.

Question 13

Which of the following is NOT a characteristic of Expansion Wave:

Accepted Answer

a. encounters a concave corner

Answer

b. Isentropic

Answer

c. Visualized as infinite number of Mach waves

Answer

d. none of the above

Question 14

This is the type of flow in which the density of the fluid elements can change from point to point.

Accepted Answer

c. Compressible Flow

Answer

a. Supersonic Flow

Answer

b. Incompressible Flow

Answer

d. Normal Flow

Question 15

The line of disturbance created along the envelope of individual wavelets

Accepted Answer

c. Mach Line

Answer

a. Boundary Line

Answer

b. Streamline

Answer

d. Chordline

Question 16

Type of Wind tunnel where the air circulates continuously within the wind tunnel where little to no exchange of air between the wind tunnel and the atmosphere.

Accepted Answer

b. Prandtl Wind Tunnel

Answer

a. Eiffel Wind Tunnel

Answer

c. Intermittent Blow-down Wind Tunnel

Answer

d. Open Return Wind Tunnel

Question 17

All of these are other names for a Closed Circuit Wind Tunnel except for:

Accepted Answer

b. Eiffel

Answer

a. Prandtl

Answer

c. Gottingen

Answer

d. Return Flow

Question 18

Compute the ambient pressure if the values of the speed of sound and ambient density is 1169 ft/s and 0.001697 slug/ft3, respectively. Assume R=1716 ft.lb/slug.R and k = 1.39.

Accepted Answer

d. 1168.384185 psf

Answer

a. 1167.384185 psf

Answer

b. 1158.384185 psf

Answer

c. 1147.384185 psf

Question 19

The gathering of leading aerodynamicists in Rome, Italy on September 30, 1935.

Accepted Answer

c. Fifth Volta Conference

Answer

a. Third Volta Conference

Answer

b. Fourth Volta Conference

Answer

d. Sixth Volta Conference

Question 20

It describes the relationship between the states on both sides of a shock wave in a one dimensional flow in fluid.

Accepted Answer

a. Rankine-Hugoniot Relations

Answer

b. Equation of State

Answer

c. Hydrostatic Equation

Answer

d. Navier-Stokes Equations

Question 21

Which of the following is in the gradient region.

Accepted Answer

b. 85280 ft

Answer

a. 39360 ft

Answer

c. 78720 ft

Answer

d. 65600 ft

Question 22

It is a thermodynamic property defined as the sum of internal energy of a system.

Accepted Answer

b. Enthalpy

Answer

a. Specific Enthalpy

Answer

c. Adiabatic

Answer

d. Compressible

Question 23

An aircraft is flying at a speed of sound of 375 m/s. If k = 1.4 and the specific gas constant is at standard condition, solve for the ambient temperature.

Accepted Answer

c. 349.8900257 K

Answer

a. 585.3521479 K

Answer

b. 558.3521479 K

Answer

d. 249.2857900 K

Question 24

It is the ratio of the specific heat at constant pressure, Cp, to the specific heat at constant volume, Cv.

Accepted Answer

d. Specific Heat Ratio

Answer

a. Perfect Gas

Answer

b. Specific Gas

Answer

c. Specific Enthalpy

Question 25

What happens when a fluid flows through an oblique shock wave?

Accepted Answer

c. Total temperature remains constant, Mach number decreases and static temperature increases.

Answer

a. Total temperature decreases, Mach number increases and static temperature decreases.

Answer

b. Total temperature remains constant, Mach number increases and static temperature increases.

Answer

d. Total temperature remains constant, Mach number decreases and static temperature remains constant.

Question 26

These wind tunnels use the appropriate design of a convergent-divergent nozzle to achieve supersonic flow.

Accepted Answer

a. Supersonic Wind Tunnels

Answer

b. Hypersonic Wind Tunnels

Answer

c. Subsonic Wind Tunnels

Answer

d. Transonic Wind Tunnels

Question 27

What is entropy and its relation to shock waves?

Accepted Answer

c. Energy that cannot be used to do useful work; entropy increases once it passes the shock wave

Answer

a. Energy that cannot be used to do useful work; entropy decreases once it passes the shock wave

Answer

b. Energy that can be used to do useful work; entropy decreases once it passes the shock wave

Answer

d. Energy that can be used to do useful work; entropy increases once it passes the shock wave

Question 28

Statements: 
1. The specific heat ratio (k) of a gas is the ratio of the specific heat at constant pressure, cp, to the specific heat at constant velocity, cv.
2. Isentropic Efficiency is sometimes referred to as the adiabatic index or the heat capacity ratio or the isentropic expansion factor or the adiabatic exponent or the isentropic exponent.

Which of the following statements are true?

Accepted Answer

d. Both are false.

Answer

a. Only 1 is true.

Answer

b. Only statement 2 is true.

Answer

c. Both are true.

Question 29

What happens to the total pressure of an upstream air after it passes a shockwave?

Accepted Answer

a. Increases

Answer

b. Decreases

Answer

c. Constant

Question 30

What type of wind tunnel incorporates a straight path into its assembly where the air goes from the entrance through a contraction portion to the test section, onto the diffuser, a fan section, and eventually onto released from the aft end as exhaust air?

Accepted Answer

a. Open Circuit Wind Tunnel

Answer

b. Return Flow Wind Tunnel

Answer

c. Intermitten Flow Wind Tunnel

Answer

d. Closed Circuit Wind Tunnel

Question 31

What kind of drag does the normal shockwave create?

Accepted Answer

a. Wave Drag

Answer

b. Viscous Drag

Answer

c. Pressure Drag

Answer

d. Lift-Induced Drag

Question 32

It is a fundamental relation derived from the fundamental laws of physics relating speed of sound, upstream velocity and downstream velocity for a shock wave.

Accepted Answer

b. Prandtl Equation

Answer

a. Rankine-Hugoniot Relations

Answer

c. Euler Equation

Answer

d. Oblique Shock Relations

Question 33

What happens to velocity and pressure in a converging subsonic wind tunnel?

Accepted Answer

a. Velocity Increases, Pressure Decreases

Answer

b. Velocity Increases, Pressure Increases

Answer

c. Velocity Decreases, Pressure Decreases

Answer

d. Velocity Decreases, Pressure Increases

Question 34

It is a centered expansion process that occurs when a supersonic flow turns around a convex corner.

Accepted Answer

a. Prandtl-Meyer Expansion Fan

Answer

b. Prandtl-Meyer Extraction Fan

Answer

c. Prandtl-Meyer Explosion Fan

Answer

d. Prandtl-Meyer Extrusion Fan

Question 35

A definite speed at which sound waves travel through the air is known as _________.

Accepted Answer

a. Speed of sound

Answer

b. Normal shockwave

Answer

c. Oblique shockwave

Answer

d. Shockwave

Question 36

What is the main characteristic of a perfect gas?

Accepted Answer

d. Its intermolecular forces are neglected

Answer

a. It has a strong intermolecular force

Answer

b. It is composed of particles with electronic structure

Answer

c. Its intermolecular forces are significant

Question 37

It is a shock wave that makes an oblique angle with respect to the upstream flow.

Accepted Answer

b. Oblique shock wave

Answer

a. Bow Shock

Answer

c. Normal shock wave

Answer

d. Expansion shock wave

Question 38

Whenever a supersonic flow is turned away from itself, a/an __________ will occur.

Accepted Answer

a. Expansion Shock Wave

Answer

b. One-Dimensional Normal Shockwave

Answer

c. Oblique Shock Wave

Answer

d. Boundary Layer

Question 39

Sometimes referred to as the adiabatic index, the heat capacity ratio, the isentropic expansion factor, the adiabatic exponent, or the isentropic exponent.

Accepted Answer

c. Specific heat ratio

Answer

a. Specific Gas Constant

Answer

b. Polytropic exponent

Answer

d. Specific heat at constant volume

Question 40

The angle at which the Mach line makes with the free stream direction

Accepted Answer

b. Mach Angle

Answer

a. Expansion Angle

Answer

c. Deflection Angle

Answer

d. Shock Wave Angle

Question 41

This type of wind tunnel uses a convergent-divergent nozzle to achieve the targeted flow.

Accepted Answer

c. Supersonic Wind Tunnel

Answer

a. Low Speed Wind Tunnel

Answer

b. Transonic Wind Tunnel

Answer

d. Hypersonic Wind Tunnel

Question 42

It is a process where no frictional or dissipate effects occur.

Accepted Answer

c. Reversible Process

Answer

a. Adiabatic Process

Answer

b. Isentropic Process

Answer

d. Irreversible Process

Question 43

It can be defined as the total energy due to pressure and temperature per unit mass.

Accepted Answer

a. Specific enthalpy (h)

Answer

b. Enthalpy (H)

Answer

c. Coefficient of Pressure

Answer

d. Coefficient of Volume

Question 44

Athodyds is the shortened term for ______________.

Accepted Answer

c. Aerothermodynamic Duct

Answer

a. Aeronautical Dynamic Duct

Answer

b. Aeronautical Thermoduct

Answer

d. Aerothermic Duct

Question 45

It is the rate at which the temperature of the atmosphere falls within latitude.

Accepted Answer

d. Lapse Rate

Answer

a. Climb Rate

Answer

b. Rate of Change

Answer

c. Temperature-Altitude Rate

Question 46

When a supersonic flow turns into itself, what is formed?

Accepted Answer

b. Oblique shock wave

Answer

a. Boundary Layer

Answer

c. Expansion shock wave

Answer

d. Turbulent flow

Question 47

Which of the following is not true about the Mach number Regimes?

Accepted Answer

b. The Mach number for subsonic flow should be higher for blunt objects

Answer

a. In transonic flow the Mach number ranges from 0.8-1.2

Answer

c. When the Mach number at every point on the object is above 1 it is considered to besupersonic

Answer

d. Shockwave angles are smaller at hypersonic speeds

Question 48

The altimeter reads 4269m calculate the pressure. (Round to the nearest whole number).

Accepted Answer

c. 59486 Pa

Answer

a. 69486 Pa

Answer

b. 58887 Pa

Answer

d. 60325 Pa

Question 49

These wind tunnels use the appropriate design of a _________ nozzle to achieve supersonic flow.

Accepted Answer

a. Convergent-divergent

Answer

b. Optimal

Answer

c. Convergent

Answer

d. Divergent

Question 50

When a system of air passes through an Oblique Shockwave, what will be the condition it conforms to?

Accepted Answer

a. Adiabatic

Answer

b. Isentropic

Answer

c. Reversible

Answer

d. Isothermal

Question 51

Flow in which the density of the fluid elements is always constant.

Accepted Answer

d. Incompressible Flow

Answer

a. Laminar Flow

Answer

b. Turbulent Flow

Answer

c. Compressible Flow

Question 52

In the physical principle: _________ can neither created nor destroyed.

Accepted Answer

b. Mass

Answer

a. Energy

Answer

c. Weight

Answer

d. Enthalpy

Question 53

It is the point where the total values are measured and where the velocity of the flow is Zero.

Accepted Answer

a. Stagnation Point

Answer

b. Center of Gravity

Answer

c. Quarter-Chord Point

Answer

d. Neutral Point

Question 54

It is defined as the ratio of the speed of the body to the speed of sound in the surrounding medium. It is primarily used to determine the approximation with which the flow can be treated as incompressible or compressible.

Accepted Answer

c. Mach Number

Answer

a. Speed of sound

Answer

b. Reynolds Number

Answer

d. Velocity

Question 55

Which of the statements is true?

1. Rankine-Hugoniot Jump Conditions describes the relationship between the states on both sides of a shock wave in a one-dimensional flow in fluid. 
2. They are named in recognition of the work carried out by William John Macquorn Rankine and Pierre Henri Hugoniot.

Accepted Answer

a. Both statements are true

Answer

b. Only statement 1 is true

Answer

c. Only statement 2 is true

Answer

d. Both statements are false

Question 56

It is a condition of a flow where there is a temperature change but no heat is being added into the system.

Accepted Answer

c. Adiabatic

Answer

a. Reversible

Answer

b. Isothermal

Answer

d. Irreversible

Question 57

In this condition, the exit pressure is less than the back pressure resulting to a high exit velocity and shockwaves forming on the exhaust plume.

Accepted Answer

d. Supersonic flow on the nozzle.

Answer

a. Subsonic flow along the nozzle

Answer

b. Subsonic flow along the nozzle but choked at the throat

Answer

c. Supersonic flow after the throat

Question 58

What is Specific Impulse a measure of?

Accepted Answer

c. The efficiency of a rocket engine-propellant combination

Answer

a. The speed of a rocket

Answer

b. The weight of a rocket engine

Answer

d. None of the above

Question 59

Which of the statements is true?

1. In a hypersonic flow, the shock layer becomes very thick and high in temperature. 
2. As the Mach number increases above 1, the shock waves move further from the body surface.

Accepted Answer

b. Both statements are false

Answer

a. Both statements are true

Answer

c. Only statement 1 is true

Answer

d. Only statement 2 is true

Question 60

These wind tunnels are designed to generate a hypersonic flow field in the working section, with speeds varying from Mach 5 to 15.

Accepted Answer

b. Hypersonic Wind Tunnels

Answer

a. Supersonic Wind Tunnels

Answer

c. Transonic Wind Tunnels

Answer

d. Sonic Wind Tunnels

Question 61

Angle between the shock wave and the upstream flow direction.

Accepted Answer

a. Wave angle

Answer

b. Angle of Attack

Answer

c. Right angle

Answer

d. Deflection angle.

Question 62

It is the ratio of inertial forces to viscous forces within a fluid which is subjected to relative internal movement due to different fluid velocities.

Accepted Answer

b. Reynolds Number

Answer

a. Speed of Sound

Answer

c. Mach Number

Answer

d. Velocity

Question 63

The speed of sound depends only on the _____ and _____ of the air.

Accepted Answer

c. Temperature; composition

Answer

a. Volume; viscosity

Answer

b. Temperature; Reynolds Number

Answer

d. Specific Heat Ratio; energy

Question 64

What is the flow upstream in both oblique shock and normal shock?

Accepted Answer

d. Supersonic

Answer

a. Subsonic

Answer

b. Hypersonic

Answer

c. Transonic

aerody

123 questions

It is determined by the altimeter and correlates to ambient pressure.

What are the three equations that will be used in deriving formulas to calculate for normal shock wave properties?

A shock wave that is unattached to the surface, staying ahead of the leading edge given specific conditions.

The sum of the energies of all the molecules in a finite volume of a gas.

In this flow, the density of the fluid is considered constant:

This is the angle to which a flow can turn isentropically for a given initial and final Mach number. This is also the maximum angle through which a sonic flow can be turned around in a convex corner.

The specific heat ratio of a gas is 1.83. Assuming that the air is at standard condition, what is the cp and cv of the gas in English units?

The ______ is the ratio of inertial forces to viscous forces within a fluid which is subjected to relative internal movement due to different fluid viscosities. It is also a dimensionless quantity that is used to determine the flow pattern while flowing through a pipe.

A Cessna 152 is flying with a velocity of 420 ft/s at a pressure altitude of 12000 ft. Given that the Mach number is 0.6, calculate for the density of air experienced by the aircraft.

It is the rate at which the temperature in the atmosphere falls with altitude

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