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Fluid Dynamics Mastery Quiz
Test your knowledge of fluid dynamics with this comprehensive quiz featuring 36 challenging questions. Designed for students and enthusiasts alike, this quiz covers topics such as compressible flow, Mach numbers, and isentropic processes.
- Multiple Choice and Checkbox questions
- Covers essential concepts and principles
- Understand the intricacies of fluid mechanics
It is also known as frictionless flow.
Inviscid flow
Viscous flow
Specific internal energy is simply internal energy expressed per unit _____.
Mass
Volume
It is a process which is both adiabatic and reversible.
Isentropic
Isothermal
A flow characterized by significant changes in the density.
Compressible
Incompressible
A dimensionless parameter defined as the ratio of the true airspeed to the local speed of sound.
Mach number
Reynolds number
In a __________, flow field variables at any given point do not change with the time.
Steady flow
Unsteady flow
Which of the following is not a dimensionless parameter?
Universal gas constant
Ratio of specific heats
If the flow velocity V exceeds speed of sound Va, then Mach number is _______.
Greater than 1
Equal to unity
The energy equation governing steady, inviscid, and adiabatic flow is:
Cp ti
Av V1
The following items contribute to an increase in the internal energy of the system except:
Work done by the system
An increase in the system's temperature
Work done on the system
Which of the following statement is true about speed of sound or sonic velocity?
It is proportional to the square root of the absolute temperature of the gas
it is inversely proportional to the pressure of the air
Speed of sound or sonic velocity in a calorically perfect gas is a function of the __________ only.
Absolute temperature
Ratio of specific heats
For Mach numbers ___________, changes in density are considered negligible. The flow can be modeled as being incompressible.
Below three-tenths
below three
Reynolds number is used in comparing flow of air at different speeds around objects of varying size. If the size of an object is decreased, what must be done to the speed of the flow to maintain the same Reynolds number? Assume other parameters are kept constant.
The speed of the flow must be increased
The speed of the flow must be decreased
In a supersonic wind tunnel, a diffuser is designed to slow down incoming gas flow to a lower velocity. In reducing the flow velocity, losses in the ______ should be kept at a minimum as much as possible.
Stagnation pressure
Static pressure
A quasi-one-dimensional flow approximates that all properties vary along _________.
x direction only
Y and z direction
Consider supersonic flow slowed down isentropically to subsonic flow in a convergent-divergent duct. At the throat (minimum area of the duct), the flow Mach number is:
Equal to one
Less than one
According to this principle, the air mass flow, or mass per unit time, will remain a constant value at all points along the tube.
Law of Continuity
Bernoulli's Theorem
Consider sonic conditions at the throat of a convergent-divergent nozzle. What is the ratio of the reservoir pressure to the throat pressure? Gas is stationary at the reservoir.
1.893
0.833
If the flow is completely isentropic in both the nozzle and the diffuser of a supersonic wind tunnel:
Total pressure remains unchanged
The total pressure is not the same for both the diffuser and the nozzle
Consider non-isentropic adiabatic flow such as in the case of a convergent-divergent nozzle with a normal shockwave downstream of its throat. Which of the following parameters remain constant throughout the nozzle?
total temperature
Total pressure
Consider isentropic flow through a convergent-divergent nozzle. Once sonic flow is achieved at the throat, which parameter assumes a limiting maximum value?
Mass flow
Exit temperature
At the point where the static pressure is minimum in the airfoil:
The pressure coefficient will have its most negative value
The pressure coefficient is equal to 0
If an aircraft is flown below its critical Mach number:
The flow is subsonic over all parts of the aircraft
The flow over the aircraft is partly subsonic and partly supersonic
For flows with Mach numbers below 0.3, a pressure coefficient of unity corresponds to a:
Stagnation point
Leading edge point
If a streamline flow of air accelerate, what happens to its static pressure?
Decrease
Increase
Which of the following is not true?
For an incompressible flow, 1.0 is the highest allowable value for the pressure coefficient
At regions where the static pressure equals the freestream pressure, the pressure coefficient is positive
For a given airfoil, the critical Mach number is the freestream Mach number at which:
The airflow reaches the speed of sound at some point in the airfoil
The flow over the entire airfoil is subsonic (M<1) only.
It is the flight speed regime from the critical Mach number up to freestream Mach numbers of 1.2:
Transonic
Hypersonic
Consider isentropic flow through a converging-diverging nozzle. If the flow remains subsonic throughout the nozzle, which of the following is true?
Downstream the throat, the Mach number decreases
Static pressure decreases from the inlet to the throat, then increases from the throat to the exit
Downstream the throat, the Mach number increases
The Mach number is minimum at the throat
It is the Mach number of the flow sufficiently remote from the aircraft/aerodynamic body, unaffected by it:
Freestream Mach number
critical Mach number
Flying at a speed greater than the critical Mach number, the lift-to-drag ratio will:
Decrease
increase
Compare two wings, one having a greater t/c ratio than the other. Which of the following is true?
The wing with the lower t/c ratio will have the greater critical Mach number
Both wings have the same critical Mach number
Considering non-compressible flows, the pressure coefficient becomes a function of __________ only.
Velocity
Mach number
Consider the variation of CP (taken at a point on an airfoil) with freestream Mach number. At subsonic freestream Mach numbers greater than 0.3, what happens to the value of CP?
The absolute magnitude increases
It approaches a value of zero
Prandtl-Glauert Rule for compressibility correction is only accurate for which of the following flows?
Subsonic flow
supersonic flow
Sonic flow
All of the choices
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