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Worksheetsaerody
Total questions: 123
Worksheet time: 2hrs 3mins
Name
Class
Date
1.
It is determined by the altimeter and correlates to ambient pressure.
a)
a. Temperature Altitude
b)
b. Density Altitude
c)
c. Pressure Altitude
d)
d. None of the Above
2.
What are the three equations that will be used in deriving formulas to calculate for normal shock wave properties?
a)
A. Mass, Momentum, & Energy Eq.
b)
B. Momentum, Perfect Gas, & Continuity Eq.
c)
C. Energy, Continuity, & Momentum Eq.
d)
D. Perfect Gas, Equation of State, Momentum Eq.
3.
A shock wave that is unattached to the surface, staying ahead of the leading edge given specific conditions.
a)
A. Expansion Wave
b)
B. Oblique Shock
c)
C. Normal Shockwaves
d)
D. Bow Shock
4.
The sum of the energies of all the molecules in a finite volume of a gas.
a)
A. Enthalpy
b)
B. Internal Energy
c)
C. Entropy
d)
D. Perfect Gas
5.
In this flow, the density of the fluid is considered constant:
a)
a. Compressible flow
b)
b. Incompressible flow
c)
c. Adiabatic flow
d)
d. Isentropic flow
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.
a)
a. Mach Angle
b)
b. Wave Angle
c)
c. Prandtl Meyer Expansion Fan
d)
d. Prandtl Meyer Function
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?
a)
a. 4783.47 ft. lb/slug.R and 3067.47 ft.lb/slug.R
b)
b. 3783.47 ft. lb/slug.R and 2067.47 ft.lb/slug.R
c)
c. 2783.47 ft. lb/slug.R and 3067.47 ft.lb/slug.R
d)
d. 2067.47 ft. lb/slug.R and 3783.47 ft.lb/slug.R
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.
a)
a. Mach Number
b)
b. Reynolds Number
c)
c. Specific Heat Ratio
d)
d. Speed of Sound
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.
a)
A. 1.65 x 10-3 kg/m3
b)
B. 5.24 x 10-3 kg/m3
c)
C. 3.85 x 10-3 slug/ft3
d)
D. 1.65 x 10-3 slug/ft3
10.
It is the rate at which the temperature in the atmosphere falls with altitude
a)
a. Temperature change rate
b)
b. Enthalpy
c)
c. Gradient rate
d)
d. Lapse rate
11.
Consider a normal shock wave where the upstream Mach number is 2. Compute for the downstream Mach number (k= 1.4).
a)
a. 0.5092
b)
b. 0.5774
c)
c. 0.8544
d)
d. 0.8321
12.
For a flow in a Subsonic Converging Nozzle, the:
a)
a. Velocity decreases; Pressure, Temperature, and Density increases.
b)
b. Velocity increases; Pressure, Temperature, and Density decreases.
c)
c. Velocity and Temperature increases; Pressure and Density decreases.
d)
d. Velocity and Temperature decreases; Pressure and Density increases.
13.
Which of the following is NOT a characteristic of Expansion Wave:
a)
a. encounters a concave corner
b)
b. Isentropic
c)
c. Visualized as infinite number of Mach waves
d)
d. none of the above
14.
This is the type of flow in which the density of the fluid elements can change from point to point.
a)
a. Supersonic Flow
b)
b. Incompressible Flow
c)
c. Compressible Flow
d)
d. Normal Flow
15.
The line of disturbance created along the envelope of individual wavelets
a)
a. Boundary Line
b)
b. Streamline
c)
c. Mach Line
d)
d. Chordline
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.
a)
a. Eiffel Wind Tunnel
b)
b. Prandtl Wind Tunnel
c)
c. Intermittent Blow-down Wind Tunnel
d)
d. Open Return Wind Tunnel
17.
All of these are other names for a Closed Circuit Wind Tunnel except for:
a)
a. Prandtl
b)
b. Eiffel
c)
c. Gottingen
d)
d. Return Flow
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.
a)
a. 1167.384185 psf
b)
b. 1158.384185 psf
c)
c. 1147.384185 psf
d)
d. 1168.384185 psf
19.
The gathering of leading aerodynamicists in Rome, Italy on September 30, 1935.
a)
a. Third Volta Conference
b)
b. Fourth Volta Conference
c)
c. Fifth Volta Conference
d)
d. Sixth Volta Conference
20.
It describes the relationship between the states on both sides of a shock wave in a one dimensional flow in fluid.
a)
a. Rankine-Hugoniot Relations
b)
b. Equation of State
c)
c. Hydrostatic Equation
d)
d. Navier-Stokes Equations
21.
Which of the following is in the gradient region.
a)
a. 39360 ft
b)
b. 85280 ft
c)
c. 78720 ft
d)
d. 65600 ft
22.
It is a thermodynamic property defined as the sum of internal energy of a system.
a)
a. Specific Enthalpy
b)
b. Enthalpy
c)
c. Adiabatic
d)
d. Compressible
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.
a)
a. 585.3521479 K
b)
b. 558.3521479 K
c)
c. 349.8900257 K
d)
d. 249.2857900 K
24.
It is the ratio of the specific heat at constant pressure, Cp, to the specific heat at constant volume, Cv.
a)
a. Perfect Gas
b)
b. Specific Gas
c)
c. Specific Enthalpy
d)
d. Specific Heat Ratio
25.
What happens when a fluid flows through an oblique shock wave?
a)
a. Total temperature decreases, Mach number increases and static temperature decreases.
b)
b. Total temperature remains constant, Mach number increases and static temperature increases.
c)
c. Total temperature remains constant, Mach number decreases and static temperature increases.
d)
d. Total temperature remains constant, Mach number decreases and static temperature remains constant.
26.
These wind tunnels use the appropriate design of a convergent-divergent nozzle to achieve supersonic flow.
a)
a. Supersonic Wind Tunnels
b)
b. Hypersonic Wind Tunnels
c)
c. Subsonic Wind Tunnels
d)
d. Transonic Wind Tunnels
27.
What is entropy and its relation to shock waves?
a)
a. Energy that cannot be used to do useful work; entropy decreases once it passes the shock wave
b)
b. Energy that can be used to do useful work; entropy decreases once it passes the shock wave
c)
c. Energy that cannot be used to do useful work; entropy increases once it passes the shock wave
d)
d. Energy that can be used to do useful work; entropy increases once it passes the shock wave
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?
a)
a. Only 1 is true.
b)
b. Only statement 2 is true.
c)
c. Both are true.
d)
d. Both are false.
29.
What happens to the total pressure of an upstream air after it passes a shockwave?
a)
a. Increases
b)
b. Decreases
c)
c. Constant
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?
a)
a. Open Circuit Wind Tunnel
b)
b. Return Flow Wind Tunnel
c)
c. Intermitten Flow Wind Tunnel
d)
d. Closed Circuit Wind Tunnel
31.
What kind of drag does the normal shockwave create?
a)
a. Wave Drag
b)
b. Viscous Drag
c)
c. Pressure Drag
d)
d. Lift-Induced Drag
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.
a)
a. Rankine-Hugoniot Relations
b)
b. Prandtl Equation
c)
c. Euler Equation
d)
d. Oblique Shock Relations
33.
What happens to velocity and pressure in a converging subsonic wind tunnel?
a)
a. Velocity Increases, Pressure Decreases
b)
b. Velocity Increases, Pressure Increases
c)
c. Velocity Decreases, Pressure Decreases
d)
d. Velocity Decreases, Pressure Increases
34.
It is a centered expansion process that occurs when a supersonic flow turns around a convex corner.
a)
a. Prandtl-Meyer Expansion Fan
b)
b. Prandtl-Meyer Extraction Fan
c)
c. Prandtl-Meyer Explosion Fan
d)
d. Prandtl-Meyer Extrusion Fan
35.
A definite speed at which sound waves travel through the air is known as _________.
a)
a. Speed of sound
b)
b. Normal shockwave
c)
c. Oblique shockwave
d)
d. Shockwave
36.
What is the main characteristic of a perfect gas?
a)
a. It has a strong intermolecular force
b)
b. It is composed of particles with electronic structure
c)
c. Its intermolecular forces are significant
d)
d. Its intermolecular forces are neglected
37.
It is a shock wave that makes an oblique angle with respect to the upstream flow.
a)
a. Bow Shock
b)
b. Oblique shock wave
c)
c. Normal shock wave
d)
d. Expansion shock wave
38.
Whenever a supersonic flow is turned away from itself, a/an __________ will occur.
a)
a. Expansion Shock Wave
b)
b. One-Dimensional Normal Shockwave
c)
c. Oblique Shock Wave
d)
d. Boundary Layer
39.
Sometimes referred to as the adiabatic index, the heat capacity ratio, the isentropic expansion factor, the adiabatic exponent, or the isentropic exponent.
a)
a. Specific Gas Constant
b)
b. Polytropic exponent
c)
c. Specific heat ratio
d)
d. Specific heat at constant volume
40.
The angle at which the Mach line makes with the free stream direction
a)
a. Expansion Angle
b)
b. Mach Angle
c)
c. Deflection Angle
d)
d. Shock Wave Angle
41.
This type of wind tunnel uses a convergent-divergent nozzle to achieve the targeted flow.
a)
a. Low Speed Wind Tunnel
b)
b. Transonic Wind Tunnel
c)
c. Supersonic Wind Tunnel
d)
d. Hypersonic Wind Tunnel
42.
It is a process where no frictional or dissipate effects occur.
a)
a. Adiabatic Process
b)
b. Isentropic Process
c)
c. Reversible Process
d)
d. Irreversible Process
43.
It can be defined as the total energy due to pressure and temperature per unit mass.
a)
a. Specific enthalpy (h)
b)
b. Enthalpy (H)
c)
c. Coefficient of Pressure
d)
d. Coefficient of Volume
44.
Athodyds is the shortened term for ______________.
a)
a. Aeronautical Dynamic Duct
b)
b. Aeronautical Thermoduct
c)
c. Aerothermodynamic Duct
d)
d. Aerothermic Duct
45.
It is the rate at which the temperature of the atmosphere falls within latitude.
a)
a. Climb Rate
b)
b. Rate of Change
c)
c. Temperature-Altitude Rate
d)
d. Lapse Rate
46.
When a supersonic flow turns into itself, what is formed?
a)
a. Boundary Layer
b)
b. Oblique shock wave
c)
c. Expansion shock wave
d)
d. Turbulent flow
47.
Which of the following is not true about the Mach number Regimes?
a)
a. In transonic flow the Mach number ranges from 0.8-1.2
b)
b. The Mach number for subsonic flow should be higher for blunt objects
c)
c. When the Mach number at every point on the object is above 1 it is considered to besupersonic
d)
d. Shockwave angles are smaller at hypersonic speeds
48.
The altimeter reads 4269m calculate the pressure. (Round to the nearest whole number).
a)
a. 69486 Pa
b)
b. 58887 Pa
c)
c. 59486 Pa
d)
d. 60325 Pa
49.
These wind tunnels use the appropriate design of a _________ nozzle to achieve supersonic flow.
a)
a. Convergent-divergent
b)
b. Optimal
c)
c. Convergent
d)
d. Divergent
50.
When a system of air passes through an Oblique Shockwave, what will be the condition it conforms to?
a)
a. Adiabatic
b)
b. Isentropic
c)
c. Reversible
d)
d. Isothermal
51.
Flow in which the density of the fluid elements is always constant.
a)
a. Laminar Flow
b)
b. Turbulent Flow
c)
c. Compressible Flow
d)
d. Incompressible Flow
52.
In the physical principle: _________ can neither created nor destroyed.
a)
a. Energy
b)
b. Mass
c)
c. Weight
d)
d. Enthalpy
53.
It is the point where the total values are measured and where the velocity of the flow is Zero.
a)
a. Stagnation Point
b)
b. Center of Gravity
c)
c. Quarter-Chord Point
d)
d. Neutral Point
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.
a)
a. Speed of sound
b)
b. Reynolds Number
c)
c. Mach Number
d)
d. Velocity
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.
a)
a. Both statements are true
b)
b. Only statement 1 is true
c)
c. Only statement 2 is true
d)
d. Both statements are false
56.
It is a condition of a flow where there is a temperature change but no heat is being added into the system.
a)
a. Reversible
b)
b. Isothermal
c)
c. Adiabatic
d)
d. Irreversible
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.
a)
a. Subsonic flow along the nozzle
b)
b. Subsonic flow along the nozzle but choked at the throat
c)
c. Supersonic flow after the throat
d)
d. Supersonic flow on the nozzle.
58.
What is Specific Impulse a measure of?
a)
a. The speed of a rocket
b)
b. The weight of a rocket engine
c)
c. The efficiency of a rocket engine-propellant combination
d)
d. None of the above
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.
a)
a. Both statements are true
b)
b. Both statements are false
c)
c. Only statement 1 is true
d)
d. Only statement 2 is true
60.
These wind tunnels are designed to generate a hypersonic flow field in the working section, with speeds varying from Mach 5 to 15.
a)
a. Supersonic Wind Tunnels
b)
b. Hypersonic Wind Tunnels
c)
c. Transonic Wind Tunnels
d)
d. Sonic Wind Tunnels
61.
Angle between the shock wave and the upstream flow direction.
a)
a. Wave angle
b)
b. Angle of Attack
c)
c. Right angle
d)
d. Deflection angle.
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.
a)
a. Speed of Sound
b)
b. Reynolds Number
c)
c. Mach Number
d)
d. Velocity
63.
The speed of sound depends only on the _____ and _____ of the air.
a)
a. Volume; viscosity
b)
b. Temperature; Reynolds Number
c)
c. Temperature; composition
d)
d. Specific Heat Ratio; energy
64.
What is the flow upstream in both oblique shock and normal shock?
a)
a. Subsonic
b)
b. Hypersonic
c)
c. Transonic
d)
d. Supersonic
65.
Which of the following is true for a Supersonic Converging tunnel?
a)
a. Velocity decreases, pressure increases
b)
b. Velocity decreases, pressure decreases
c)
c. Velocity increases, pressure increases
d)
d. Velocity increases, pressure decreases
66.
Which of the following choices is correct?
I. The flow upstream in both oblique and normal shock wave are supersonic
II. The flow downstream in normal shock is subsonic
III. The flow downstream in oblique shock is supersonic
a)
a. Statement I and III are false
b)
b. Only statement II is true
c)
c. Only statement III is false
d)
d. Statement I and II are false
67.
This regime is also called a mixed region because it has 2 different regimes happening at the same time. it has pockets of supersonic flow over both the top and bottom surfaces of the airfoil. Moreover, if M is increased slightly above unity, a bow shock wave is formed in front of the body.
a)
a. Subsonic
b)
b. Supersonic
c)
c. Transonic
d)
d. Hypersonic
68.
What is the exit velocity of a divergent duct with an inlet area of 5 m2 and exit area of 11 m2 where the air entering the duct has a velocity of 89 m/s?
a)
a. 40.4545 m/s
b)
b. 43.1818 m/s
c)
c. 37.0833 m/s
d)
d. 48.5455 m/s
69.
Consider a normal shock wave with a velocity of 1500 m/s and a temperature of 400 K. What is the Mach number behind the shock?
a)
a. 3.7411
b)
b. 3.7410
c)
c. 3.7511
d)
d. 3.7510
70.
The decrease in temperature with height in the Earth's lower atmosphere.
a)
a. Isothermal Region
b)
b. Lapse rate
c)
c. Energy Equation
d)
d. Gradient Ratio
71.
The flight test data for a given airplane refer to a level flight maximum velocity run made at an altitude which simultaneously corresponded to a pressure altitude of 30,000 ft. and a density altitude of 28,500 ft. Calculate the temperature of the air at the altitude at which the airplane was flying for the test.
a)
a. 389.69 R
b)
b. 379.95 R
c)
c. 399.65 R
d)
d. 391.977 R
72.
What is the heat capacity ratio if the specific heat at constant pressure of air is 1107 and air is at standard condition?
a)
a. 1.3501
b)
b. 1.3988
c)
c. 1.3503
d)
d. 1.3900
73.
Across the expansion wave, the Mach number ____, while the pressure, temperature, and density ____.
a)
a. increases, increase
b)
b. decreases, increase
c)
c. decreases, decrease
d)
d. increases, decrease
74.
It is an algebraic equation that relates the values of area, density, and velocity at one section of the stream tube to the same quantities at any other section along the stream tube?
a)
a. Mass flow Equation
b)
b. Bernoulli’s Equation
c)
c. Continuity Equation
d)
d. Hydrostatic Equation
75.
Which of these is incorrect for the normal shock wave analysis?
a)
a. No viscous effects or body forces
b)
b. Adiabatic Flow
c)
c. Differential Form of conservation equations used
d)
d. Steady Flow
76.
Describes the relationship between the states on both sides of a shock wave in a one-dimensional flow in fluid.
a)
a. Isentropic Flow Conditions
b)
b. Energy Equation
c)
c. Rankine-Hugoniot Conditions
d)
d. Momentum Equation
77.
What is the Mach Number of an airplane flying at 850 ft/s in air at 485R? Specific gas constant is equal to 1716 ft.lb/slug.R.
a)
a. 0.7875
b)
b. 0.7777
c)
c. 0.7117
d)
d. D. 0.7177
78.
Consider a Mach Number of 3.1 in a normal shockwave. Compute for its density, pressure, and temperature ratios across the shock. (kair = 1.4) (Format: Density, Pressure, Temperature Ratios)
a)
a. 4.7966, 11.5978, 1.0486
b)
b. 3.9466, 11.045, 2.7986
c)
c. 2.498, 10.9765, 1.579
d)
d. 3.5978, 12.079, 2.5976
79.
Which of these statements is NOT correct?
a)
a. Specific Impulse is a measurement of efficiency of a rocket engine – propellant combination
b)
b. Thrust is the force that moves the rocket through the air and through space
c)
c. Static Pressure is a type of pressure we would feel if we were moving along with the flow at that point
d)
d. Total Pressure is where the velocity of the flow is zero.
80.
An aircraft is flying at an altitude of 9 kilometers from the ground. Now, simply compute the pressure. Where Po and To are at SSLC.
a)
a. 37015.1307 Pa
b)
b. 31705.1309 Pa
c)
c. 30715.1309 Pa
d)
d. 30175.1307 Pa
81.
A type of wind tunnel where the air flowing recirculates with little or no exchange of air with the exterior.
a)
a. Return Flow
b)
b. Open Circuit
c)
c. Supersonic
d)
d. Transonic
82.
Which of the following best describes an isentropic flow?
a)
a. There is no heat added or taken away
b)
b. No friction
c)
c. Both A and B
d)
d. None of the above
83.
Which of the following is NOT a special optical system used in capturing shock waves (photographs)?
a)
a. Shadowgraphs
b)
b. Schlieren
c)
c. Borescopes
d)
d. Interferometers
84.
Which of the following is not a constraint for wind tunnel and reservoir calculations?
a)
a. Steady Flow
b)
b. Perfect Gas
c)
c. Quasi-one dimensional flow
d)
d. Adiabatic Flow
85.
An aircraft is flying at an altitude where the pressure and density are 2100 psf and 0.0022 slug/ft3 , respectively. What is the temperature if the specific gas constant is equal to 1716 ft.lb/slug.oR?
a)
a. 556 R
b)
b. 665 R
c)
c. 565 R
d)
d. 656 R
86.
Sound waves travel through the air at a definite speed.
a)
a. Speed of Sound
b)
b. Mach Number
c)
c. Reynold’s Number
d)
d. Velocity
87.
Which is/are not a characteristic of an expansion wave?
a)
a. Infinite number of Mach waves
b)
b. No viscous effects on the sides of control volume
c)
c. Turned into itself
d)
d. Both b and c
88.
It is described as a perfect gas exhibiting constant specific heat capacities.
a)
a. Thermally Perfect Gas
b)
b. Calorically Perfect Gas
c)
c. Calorically Imperfect Gas
d)
d. None of the Above
89.
This is a type of low speed wind tunnel where flowing air follows a straight path from the entrance through a contraction to the test section, followed by a diffuser, a fan section, and an exhaust of the air.
a)
a. Gottlingen
b)
b. Prandtl
c)
c. Return Flow
d)
d. Eiffel
90.
It is known as the direct antithesis of a shock wave
a)
a. Oblique shock wave
b)
b. Reflected Oblique shock wave
c)
c. Expansion wave
d)
d. Reflected shock wave
91.
A uniform supersonic flow at Mach 2.4 with static pressure of 74000 Pa and a temperature of 249K expands around 9-degree convex corner. Determine the downstream Mach Number.
a)
a. 2.9
b)
b. 2.8
c)
c. 2.7
d)
d. 2.6
92.
What sonic speed should we take into account for it to transition to hypersonic speed?
a)
a. Mach 3
b)
b. Mach 4
c)
c. Mach 5
d)
d. Mach 6
93.
Which among these are not a characteristic of a normal shock wave?
a)
A. steady flow
b)
B. adiabatic
c)
C. has viscous effects on the sides of the control volume
d)
D. kinetic energy is converted to internal energy.
94.
In a subsonic flow, the total pressure that is being measured by a pitot tube is:
a)
a. freestream total pressure
b)
b. total pressure in front of the shock wave
c)
c. total pressure behind the shock wave
95.
It is a function of the sum of the squares of the leading and trailing edge semi-wedges angles, and it may readily be shown that this is a minimum when the airfoil is completely symmetrical
a)
a. viscous drag
b)
b. lift to drag coefficient
c)
c. drag coefficient
d)
d. parasite
96.
Which of the following statements is true regarding oblique shockwaves?
a)
a. Across an oblique shockwave, the Mach number discontinuously increases.
b)
b. Across an oblique shockwave, the pressure, density, and temperature discontinuously decrease.
c)
c. An oblique shockwave occurs whenever a supersonic flow is “turned into itself”
d)
d. An oblique shockwave occurs when a supersonic flow passes through a convex corner and the streamlines are turned away from the main bulk of the flow.
97.
It is the process wherein there is both no heat is added or taken away and no frictional or other dissipative effects occur.
a)
A. Adiabatic Process
b)
B. Reversible Process
c)
C. Isentropic Process
d)
D. Isothermal Process
98.
These wind tunnels are used for low-speed flows, where Mach number is less than 0.3, and on computations, are assumed to be incompressible.
a)
a. Low speed wind tunnel
b)
b. Transonic wind tunnel
c)
c. Supersonic wind tunnel
d)
d. Hypersonic wind tunnel
99.
It describes the relationship between the states on both side of a shock wave in one dimension flow in fluid
a)
a. Momentum Equation
b)
b. Prandtl equation
c)
c. Energy Equation
d)
d. Rankine-Hugoniot Jump Conditions
100.
The angle between the shock wave and the upstream flow direction
a)
a. Deflection angle
b)
b. Mach angle
c)
c. Reflected angle
d)
d. Wave angle
101.
It is the pressure at a given point in a flow that would exist if the flow were slowed down isentropically to zero velocity at that point.
a)
a. Dynamic pressure
b)
b. Total pressure
c)
c. Static Pressure
d)
d. Atmospheric pressure
102.
This will occur when supersonic flow is “turned into itself”
a)
A. Expansion wave
b)
B. Mach wave
c)
C. Normal shock wave
d)
D. Oblique shock wave
103.
A shock wave that is unattached to the surface, staying ahead of the leading edge given specific conditions
a)
A. Normal Shock
b)
B. Bow Shock
c)
C. Oblique Shock
d)
D. Reflected Shock
104.
How many throats are present in a supersonic wind tunnel?
a)
a. 1
b)
b. 3
c)
c. 2
d)
d. 4
105.
This describes the relationship between the states on both sides of a shockwave in a one-dimensional flow of a fluid.
a)
A. Rankine-Hugoniot Jump Conditions
b)
B. Prandtl Equation
c)
C. Reynolds Number
d)
D. Prandtl Meyer Function
106.
This can occur at any value of M > 1, but the value of θ at which it occurs increases as M increases?
a)
A. Shock Detachment
b)
B. Bow Shock
c)
C. Oblique Shock
d)
D. Normal Shock
107.
Which of the following is NOT true regarding the important physical facts about NSW/OSW from?
a)
A. It has viscous effects on the sides of the control volume.
b)
B. It has NO viscous effects on the sides of the control volume.
c)
C. It is Adiabatic
d)
D. It is Steady
108.
It is usually generated at the trailing edge, sometimes in a “fishtail” pattern.
a)
a. Bow shock wave
b)
b. Normal shock wave
c)
c. Weak shock wave
d)
d. Oblique shock wave
109.
At Subsonic flight regime, the density decreases as the Mach number __________.
a)
a. Decreases
b)
b. Remains constant
c)
c. Increases
d)
d. Has a negative value
110.
Flow Downstream in Oblique shock
a)
A. Reduced speed but still supersonic
b)
B. Forms a bow shock
c)
C. Reduced speed but subsonic
d)
D. Speed is increased
111.
It is sometimes referred to as the adiabatic index or the isentropic expansion factor or the adiabatic exponent or the isentropic exponent.
a)
A. Specific Heat Ratio (k)
b)
B. Specific Heat at constant pressure (Cp)
c)
C. Specific Heat at constant volume (Cv)
d)
D. Gas Constant (R)
112.
Downstream of the expansion fan the Mach number _______ and the pressure, density, and
temperature _______.
a)
A. increases, decreases
b)
B. decreases, increases
c)
C. increases, increases
d)
D. decreases, decreases
113.
A shortened term for Aerothermodynamic Duct
a)
a. Athodyd
b)
d. Adhotyd
c)
c. Aethodid
d)
d. Aeroduct
114.
Which of the following is NOT true
a)
A. Flow Upstream in Oblique Shock = Supersonic
b)
B. Flow Upstream in Normal Shock = Subsonic
c)
C. Flow Downstream in Oblique Shock = Supersonic
d)
D. Flow Downstream in Normal Shock = Subsonic
115.
Occurs when the shock wave moves closer to the body surface as the Mach number increases more than 1?
a)
A. Shock wave strength decreases
b)
B. Shock wave strength stays the same
c)
C. Shock wave strength increases
d)
D. Shock wave formation dissipates
116.
What happens to the flow velocity and temperature in an oblique shockwave in aerodynamics?
a)
A) The velocity decreases and the temperature increases
b)
B) The velocity increases and the temperature decreases
c)
C) The velocity decreases and the temperature decreases
d)
D) The velocity increases and the temperature increases
117.
Which of the following is determined by the altimeter and refers to the pressure of the
surrounding environment?
a)
A) Temperature Altitude
b)
B) Density Altitude
c)
C) Pressure Altitude
d)
D) None of the Above
118.
Which of the following statements is TRUE?
a)
A. Subsonic - M > 1
b)
B. Transonic - M = 1.2
c)
C. Sonic - M = 1
d)
D. Supersonic - M < 2
119.
It is a type of flow in which the density of the fluid elements is always constant.
a)
a) Incompressible Flow
b)
b) Compressible Flow
c)
c) Isentropic Flow
d)
d) Viscous Flow
120.
A type of Low-Speed Wind Tunnel where the airflow recirculates with little or no exchange of air with the exterior.
a)
a. Open Circuit
b)
b. Eiffel
c)
c. Return Flow
d)
d. NPL
121.
To create the desired flow, this wind tunnel employs a convergent-divergent nozzle.
a)
a. Supersonic Wind Tunnel
b)
b. Transonic Wind Tunnel
c)
c. Subsonic Wind Tunnel
d)
d. Hypersonic Wind Tunnel
122.
What is the temperature of the standard atmosphere at 11km?
a)
a. 287.08 K
b)
b. 288.16 K
c)
c. 216.66 K
d)
d. 519 K
123.
The free-stream Mach number at which sonic flow is first obtained somewhere on the airfoil surface is called the __________________ of the airfoil.
a)
a. Upstream Mach Number
b)
b. Sonic Mach Number
c)
c. Critical Mach Number
d)
d. Downstream Mach Number
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