B.TechSemester 62023-24Gas Dynamics And Jet PropulsionKME064
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Gas Dynamics And Jet Propulsion (KME064) - AKTU Question Paper 2023-24

B.Tech · Semester 6 · Free PDF Download

This is the official AKTU Gas Dynamics And Jet Propulsion Previous Year Question Paper for B.Tech Semester 6, academic session 2023-24. Published by Dr. A.P.J. Abdul Kalam Technical University (AKTU/UPTU), Lucknow. Free PDF download — no login required.

Course:B.Tech
Semester:Semester 6
Session:2023-24
University:AKTU / UPTU

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Questions Asked in 2023-24

Gas Dynamics And Jet Propulsion (KME064) — extracted question text · 100 marks · 3 Hours

Section AAttempt all questions in brief. 2 x 10 = 20
  • a
    State the term compressibility effect. 02
  • b
    Differentiate nozzle and diffuser. 02
  • c
    Express the stagnation enthalpy in terms of static enthalpy and velocity of flow? 02
  • d
    State the reason for development of shock wave in nozzle. 02
  • e
    What are conditions to be satisfied by Fanno Flow 02
  • f
    Explain over-expanded and under expanded flow 02
  • g
    What is Escape velocity. 02
  • h
    Explain essential components of turbojet engines 02 i. What do you mean by By-Pass ratio in Turbofan engines. 02 j. What is monopropellant? Give one example 02
Section BAttempt any three of the following: 3 x 10 = 30
  • a
    Derive the expression for stagnation to static temperature ratio and Mach number of flow
  • b
    Draw the variation of Mach number along the length of a convergent -divergent duct when it acts as a (a) Nozzle (b) Diffuser (c) Venturi
  • c
    Prove that the Mach number of FANNO LINE for maximum entropy is 1. 10
  • d
    With a neat sketch & thermodynamic cycle explain the working RAMJET engine and derive the equation for thrust developed
  • e
    What are the advantages and disadvantages of liquid propellants compared to solid propellants
Section CAttempt any one part of the following: 1 x 10 = 10
  • a
    Show that for sonic flow the deviation between the compressible and incompressible flow values of the pressure coefficient of a percent gas (γ =1.4) is about 27.5 percent
  • b
    Derive the following relations for one-dimensional isentropic flow
  • a
    Examine the variation of Mach number, static and stagnation pressure across a normal shock
  • b
    The effective jet exit velocity from a jet engine is 2700m/s. The forward flight speed is 1350m/s and airflow rate is 78.6 kg/s. solve for following
  • c
    Propulsive efficiency
  • a
    Discuss in detail the various propellants used in solid fuel rockets and liquid fuel system. Also sketch the propellant feed-system for a liquid propellant rocket motor
  • b
    Prove that when the Rayleigh flow is subsonic (Ma<1), fluid heating ( δq>0) increases fluid velocity while fluid cooling decreases fluid velocity
  • a
    Air (γ =1.4,R=287.43 J/Kg K) enters a straight axis -symmetric duct at 300 K,3.45 bar and150 m/s and leaves it at 277 k,500cm² . Assuming adiabatic flow determines
  • 1
    stagnation temperature
  • 4
    area of the cross-section at exit
  • b
    Discuss what is meant by thrust augmentation and explain how it is affected 10
  • a
    Discuss the working of basic components of aircraft gas turbine engines. Also draw T-S diagram of Brayton cycle
  • b
    A rocket flies at 10,080 Kmph with an effective exhaust jet velocity of 1400m/s and propellant flow rate of 5.0Kg/s. If the heat of reaction of the propellants is 6500KJ/Kg of the propel at mixture determine
  • a
    Propulsion efficiency and propulsion power
  • b
    Engine output and thermal efficiency, and

Question text is extracted from the official AKTU question paper PDF above. Check the original PDF for equations, diagrams and complete wording. Extracted: 2026-08-23.

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