Supersonic MCQs Aeronautical Engineering

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In supersonic flow, the flow velocity is:

A) Less than the speed of sound
B) Equal to the speed of sound
C) Greater than the speed of sound
D) Zero
Answer: C) Greater than the speed of sound
The primary effect of a shock wave in supersonic flow is:

A) Decreased pressure
B) Increased temperature
C) Increased drag
D) Decreased lift
Answer: C) Increased drag
Which of the following best describes a Mach cone?

A) A cone-shaped disturbance created by an object moving through a medium at supersonic speeds
B) A conical shape used in subsonic wind tunnels
C) A tool for measuring aerodynamic drag
D) A shape used to create laminar flow
Answer: A) A cone-shaped disturbance created by an object moving through a medium at supersonic speeds
The ‘drag polar’ of a supersonic aircraft typically shows:

A) Increased drag at higher speeds
B) Decreased drag at higher speeds
C) No change in drag with speed
D) Reduced drag at low speeds
Answer: A) Increased drag at higher speeds
In supersonic flight, which of the following is true about the pressure distribution around the aircraft?

A) Pressure decreases continuously around the aircraft
B) Pressure increases continuously around the aircraft
C) Pressure increases then decreases around the aircraft
D) Pressure is constant around the aircraft
Answer: A) Pressure decreases continuously around the aircraft
The term ‘wave drag’ in supersonic aerodynamics refers to:

A) The drag associated with shock waves and pressure differences
B) The drag due to skin friction
C) The drag caused by turbulence
D) The drag resulting from airfoil shape
Answer: A) The drag associated with shock waves and pressure differences
In supersonic flight, the ‘Prandtl-Glauert transform’ is used to:

A) Convert subsonic data to supersonic conditions
B) Predict shock wave positions
C) Calculate drag coefficients
D) Assess thermal loads
Answer: A) Convert subsonic data to supersonic conditions
A ‘bow shock’ in supersonic flow occurs:

A) Around the leading edge of a supersonic object
B) At the trailing edge of a subsonic object
C) On the upper surface of an aircraft wing
D) At the boundary layer separation point
Answer: A) Around the leading edge of a supersonic object
Which design feature is crucial for supersonic aircraft to minimize drag?

A) Sharp leading edges
B) Large aspect ratio wings
C) Thick airfoils
D) High wing sweep angles
Answer: D) High wing sweep angles
In supersonic flow, the Mach number is defined as:

A) The ratio of the object’s speed to the speed of sound in the medium
B) The ratio of the object’s speed to the object’s weight
C) The ratio of pressure to temperature
D) The ratio of the object’s thrust to drag
Answer: A) The ratio of the object’s speed to the speed of sound in the medium
The term ‘Mach number’ is used to describe:

A) The ratio of flow velocity to the speed of sound
B) The ratio of drag to lift
C) The ratio of pressure to altitude
D) The ratio of temperature to pressure
Answer: A) The ratio of flow velocity to the speed of sound
In supersonic flight, the ‘shock wave strength’ is influenced by:

A) The Mach number and the pressure difference
B) The aircraft’s weight
C) The altitude of the aircraft
D) The engine thrust
Answer: A) The Mach number and the pressure difference
The ‘sonic boom’ produced by supersonic aircraft is caused by:

A) The abrupt pressure changes associated with shock waves
B) The high-speed airflow around the aircraft
C) The vibration of aircraft surfaces
D) The exhaust noise from the engines
Answer: A) The abrupt pressure changes associated with shock waves
The ‘sweepback angle’ of a supersonic wing helps to:

A) Reduce drag and manage shock waves
B) Increase lift and maneuverability
C) Enhance stability at low speeds
D) Improve fuel efficiency
Answer: A) Reduce drag and manage shock waves
In supersonic aerodynamics, ‘compressibility effects’ refer to:

A) The changes in density and pressure of the air as it flows over the aircraft
B) The reduction in drag due to airfoil design
C) The increased efficiency of high-speed engines
D) The effect of air temperature on engine performance
Answer: A) The changes in density and pressure of the air as it flows over the aircraft
In supersonic flight, the ‘shock wave’ is typically:

A) Normal to the direction of flow
B) Parallel to the direction of flow
C) Perpendicular to the direction of flow
D) Formed at the trailing edge of the aircraft
Answer: A) Normal to the direction of flow
The ‘transonic region’ is characterized by:

A) A mixture of subsonic and supersonic flow around the aircraft
B) Purely supersonic flow throughout the aircraft
C) Completely laminar flow conditions
D) Subsonic flow only
Answer: A) A mixture of subsonic and supersonic flow around the aircraft
In supersonic flight, the ‘wave drag’ is primarily caused by:

A) Shock waves and pressure drag
B) Skin friction and turbulence
C) Induced drag and parasitic drag
D) Lift-induced drag and form drag
Answer: A) Shock waves and pressure drag
The ‘Mach angle’ is the angle between:

A) The direction of the shock wave and the direction of the object’s motion
B) The aircraft’s wing and the fuselage
C) The airflow and the aircraft’s centerline
D) The shock wave and the wing surface
Answer: A) The direction of the shock wave and the direction of the object’s motion
The ‘wave drag’ on a supersonic aircraft can be reduced by:

A) Using a streamlined shape and high-speed design
B) Increasing the wing area and thickness
C) Enhancing engine thrust and performance
D) Using larger control surfaces
Answer: A) Using a streamlined shape and high-speed design
The ‘shock-expansion theory’ helps in:

A) Predicting changes in flow properties due to shock waves and expansions
B) Calculating fuel consumption rates
C) Designing wing structures for high-speed flight
D) Assessing thermal stresses on aircraft
Answer: A) Predicting changes in flow properties due to shock waves and expansions
A ‘normal shock wave’ in supersonic flow is characterized by:

A) A perpendicular shock wave to the flow direction
B) An oblique shock wave forming at high angles
C) No change in flow properties across the shock wave
D) The flow remaining supersonic after crossing the shock wave
Answer: A) A perpendicular shock wave to the flow direction
The ‘drag divergence Mach number’ is:

A) The Mach number at which drag increases significantly due to shock wave formation
B) The Mach number where drag is minimized
C) The Mach number at which lift begins to decrease
D) The Mach number at which the aircraft stalls
Answer: A) The Mach number at which drag increases significantly due to shock wave formation
In supersonic flight, the ‘shock wave’ interaction with the boundary layer can lead to:

A) Flow separation and increased drag
B) Improved aerodynamic efficiency
C) Decreased drag and turbulence
D) Enhanced lift and maneuverability
Answer: A) Flow separation and increased drag
The ‘Mach number’ at which shock waves begin to form on the surface of the aircraft is known as:

A) The critical Mach number
B) The design Mach number
C) The drag divergence Mach number
D) The maximum Mach number
Answer: A) The critical Mach number
In supersonic flight, ‘wave drag’ is significantly influenced by:

A) The shape of the aircraft and the speed of sound
B) The temperature of the air and engine performance
C) The aircraft’s weight and altitude
D) The angle of attack and wing loading
Answer: A) The shape of the aircraft and the speed of sound
The ‘Area Rule’ in supersonic aircraft design aims to:

A) Minimize drag by ensuring smooth transitions in cross-sectional area
B) Increase the wing loading for better stability
C) Enhance engine efficiency by optimizing intake shapes
D) Improve structural integrity by using advanced materials
Answer: A) Minimize drag by ensuring smooth transitions in cross-sectional area
The ‘transonic drag rise’ phenomenon occurs:

A) As the aircraft transitions from subsonic to supersonic speeds
B) During subsonic flight at high angles of attack
C) When the aircraft reaches its maximum altitude
D) At low speeds with high thrust settings
Answer: A) As the aircraft transitions from subsonic to supersonic speeds
The ‘supersonic flow’ characteristics include:

A) Formation of shock waves and expansion fans
B) Smooth, continuous flow without shock waves
C) Increased lift and decreased drag
D) Uniform temperature and pressure distributions
Answer: A) Formation of shock waves and expansion fans
In supersonic aerodynamics, the term ‘shock wave’ refers to:

A) A sudden and discontinuous change in flow properties
B) A gradual change in pressure across the aircraft
C) A smooth transition in airflow over the wing
D) A steady increase in temperature
Answer: A) A sudden and discontinuous change in flow properties
The ‘sweepback angle’ of a supersonic wing helps to:

A) Manage shock waves and reduce drag
B) Increase lift at low speeds
C) Enhance stability during turbulence
D) Improve fuel efficiency in subsonic flight
Answer: A) Manage shock waves and reduce drag
Supersonic aircraft often use ‘delta wings’ to:

A) Improve performance at high speeds and reduce drag
B) Increase lift at low speeds and high angles of attack
C) Enhance maneuverability in turbulent conditions
D) Optimize fuel consumption during cruise
Answer: A) Improve performance at high speeds and reduce drag
The ‘Prandtl-Glauert rule’ is used to:

A) Predict transonic flow characteristics from subsonic data
B) Calculate the drag coefficient of supersonic aircraft
C) Determine shock wave angles in supersonic flow
D) Assess the thermal stresses on aircraft surfaces
Answer: A) Predict transonic flow characteristics from subsonic data
A ‘strong shock wave’ is characterized by:

A) Large pressure differences and rapid deceleration of flow
B) Small pressure differences and gradual flow changes
C) Minimal impact on drag and lift
D) No effect on the aircraft’s performance
Answer: A) Large pressure differences and rapid deceleration of flow
The ‘Mach number’ at which the drag coefficient starts to increase significantly is known as:

A) The drag divergence Mach number
B) The critical Mach number
C) The maximum Mach number
D) The design Mach number
Answer: A) The drag divergence Mach number
The ‘supersonic wind tunnel’ is used to:

A) Simulate high-speed flow conditions for aerodynamic testing
B) Measure the performance of subsonic aircraft
C) Assess fuel efficiency in low-speed environments
D) Evaluate noise levels of jet engines
Answer: A) Simulate high-speed flow conditions for aerodynamic testing
The ‘shock wave boundary layer interaction’ can cause:

A) Increased drag and potential flow separation
B) Improved aerodynamic efficiency and lift
C) Reduced turbulence and smoother flow
D) Enhanced fuel efficiency and engine performance
Answer: A) Increased drag and potential flow separation
The ‘Mach cone angle’ can be calculated using:

A) The inverse sine of the reciprocal of the Mach number
B) The cosine of the Mach number
C) The tangent of the Mach number
D) The logarithm of the Mach number
Answer: A) The inverse sine of the reciprocal of the Mach number
The ‘area rule’ helps to reduce drag by:

A) Ensuring smooth changes in cross-sectional area
B) Increasing the aspect ratio of the wings
C) Optimizing engine thrust
D) Enhancing control surface effectiveness
Answer: A) Ensuring smooth changes in cross-sectional area
In supersonic flight, ‘oblique shock waves’ are:

A) Shock waves that form at an angle to the flow direction
B) Perpendicular shock waves to the flow direction
C) Waves that do not affect the flow properties
D) Smooth, continuous changes in flow conditions
Answer: A) Shock waves that form at an angle to the flow direction
The ‘Ramjet’ engine is effective in supersonic flight because:

A) It uses the high-speed air flow to compress the intake air
B) It requires high-speed rotating blades for compression
C) It operates efficiently only at subsonic speeds
D) It generates thrust through a series of combustor stages
Answer: A) It uses the high-speed air flow to compress the intake air
In supersonic aerodynamics, ‘expansion fans’ are used to:

A) Accelerate the flow and reduce pressure behind a shock wave
B) Slow down the flow and increase pressure
C) Create shock waves to enhance lift
D) Stabilize the aircraft during turbulence
Answer: A) Accelerate the flow and reduce pressure behind a shock wave
Supersonic aircraft often have ‘canard’ designs to:

A) Improve control and stability at high speeds
B) Increase the overall weight of the aircraft
C) Enhance fuel efficiency during takeoff
D) Reduce the drag caused by the main wings
Answer: A) Improve control and stability at high speeds
The ‘shock wave strength’ increases with:

A) Increasing Mach number and pressure difference
B) Decreasing Mach number and temperature
C) Increasing altitude and air density
D) Decreasing speed and aerodynamic drag
Answer: A) Increasing Mach number and pressure difference
The ‘critical Mach number’ is:

A) The Mach number at which shock waves begin to form on the aircraft
B) The Mach number where drag is minimized
C) The Mach number at which the aircraft reaches maximum speed
D) The Mach number for optimal fuel efficiency
Answer: A) The Mach number at which shock waves begin to form on the aircraft
In supersonic aerodynamics, ‘shock wave drag’ is primarily due to:

A) The abrupt change in pressure and temperature across the shock wave
B) The smooth transition of airflow over the aircraft
C) The gradual change in air density
D) The reduced engine thrust at high speeds
Answer: A) The abrupt change in pressure and temperature across the shock wave
The ‘shock-expansion theory’ is used to analyze:

A) The behavior of shock waves and expansion fans in supersonic flow
B) The flow characteristics in subsonic conditions
C) The performance of low-speed aircraft
D) The efficiency of jet propulsion systems
Answer: A) The behavior of shock waves and expansion fans in supersonic flow
Supersonic aircraft typically employ ‘variable geometry wings’ to:

A) Adjust the wing shape for optimal performance at different speeds
B) Increase drag at high speeds
C) Reduce control surface effectiveness
D) Enhance stability at low speeds
Answer: A) Adjust the wing shape for optimal performance at different speeds
The ‘drag coefficient’ of a supersonic aircraft is influenced by:

A) The shape of the aircraft and the Mach number
B) The engine thrust and fuel consumption
C) The altitude and air temperature
D) The wing loading and control surfaces
Answer: A) The shape of the aircraft and the Mach number
The ‘sonic boom’ produced by a supersonic aircraft is a result of:

A) The rapid pressure changes caused by shock waves reaching the ground
B) The smooth, continuous flow of air around the aircraft
C) The gradual increase in speed as the aircraft accelerates
D) The reduction in drag as the aircraft transitions to supersonic speeds
Answer: A) The rapid pressure changes caused by shock waves reaching the ground

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