JNTU
JNTU B.Tech III AERODYNAMICS II Previous Question Paper (May - 2018 - R13)
Note: This question paper contains two parts A and B. Part A is compulsory which carries 25 marks. Answer all questions in Part A. Part B consists of 5 Units. Answer any one full question from each unit. Each question carries 10 marks and may have a, b, c as sub questions.
Part A
Under what conditions, the work transfer between a closed system and its surroundings becomes equal to
Answer
The work transfer is equal to the integral of p dv when the process is quasi-static (or internally reversible) and the system is closed, meaning no mass crosses the boundary.
Can entropy change due to internal reversibility be negative? Justify.
Answer
No, the entropy change due to internal reversibility cannot be negative. By the Clausius inequality, for any internally reversible process, the entropy change is defined as
For air at a stagnation temperature of 1000 K, find the maximum attainable velocity?
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Consider a flow with a pressure and temperature of 1 atm and 288 K. A pitot tube is inserted in to this flow and measures a pressure of 1.555 atm. What is the velocity of the flow?
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What is the maximum value of Prandtl-Meyer angle for a given flow if the initial Mach number is very large?
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What is the effect of compressibility on the shock detachment distance from the body?
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What is critical Mach number?
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Can an isentropic flow be geometrically choked multiple times in a given shaped duct?
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What is a hypersonic flow?
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What are the boundary conditions for a linearized supersonic flow?
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Part B
Explain the principle of increase of entropy.
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One kg of water at 273 K is brought into contact with a heat reservoir at 373 K. When the water has reached 373 K, find the entropy change of the water, of the heat reservoir, and of the universe.
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Show that for a reversible flow adiatic process executed by an ideal gas the following relations hold good: a)
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Derive an expression for area ratio
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The flow upstream of a normal shock wave is 1 atm. The pressure and temperature downstream of the wave are 10.33 atm and 772.2 K. Calculate the Mach number and temperature upstream of the wave and the total temperature and total pressure downstream of the wave.
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An oblique shock wave is formed when a supersonic flow with a Mach number of 2.0 is deflected inward by a concave corner having a deviation angle of 15o. Find out the Mach number downstream of the shock, if the wave is a (a) strong wave and (b) weak wave.
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Explain why two oblique shock solutions are possible for a given flow turning angle and incoming flow Mach number? Justify your explanation using appropriate expressions.
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Explain how does a shock wave developed in the diverging section of a supersonic nozzle? When does this wave move towards the exit?
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Derive the linearized velocity potential equation for a two dimensional, irrotational, isentropic flow.
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Consider an infinitely thin flat plate at an angle of attack α in a Mach 2.6 flow. Calculate the lift and wave drag coefficients for a) α = 5o b) α = 10o c) α = 30o using linear theory.
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Explain the implementation of method of characteristics to supersonic nozzle design.
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