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.
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Questions Asked in 2023-24
Gas Dynamics And Jet Propulsion (KME064) — complete question paper · 100 marks · 3 Hours
- aState the term compressibility effect. 02
- bDifferentiate nozzle and diffuser. 02
- cExpress the stagnation enthalpy in terms of static enthalpy and velocity of flow? 02
- dState the reason for development of shock wave in nozzle. 02
- eWhat are conditions to be satisfied by Fanno Flow 02
- fExplain over-expanded and under expanded flow 02
- gWhat is Escape velocity. 02
- hExplain 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
- aDerive the expression for stagnation to static temperature ratio and Mach number of flow
- bDraw the variation of Mach number along the length of a convergent -divergent duct when it acts as a (a) Nozzle (b) Diffuser (c) Venturi
- cProve that the Mach number of FANNO LINE for maximum entropy is 1. 10
- dWith a neat sketch & thermodynamic cycle explain the working RAMJET engine and derive the equation for thrust developed
- eWhat are the advantages and disadvantages of liquid propellants compared to solid propellants
- aShow 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
- bDerive the following relations for one-dimensional isentropic flow
- aExamine the variation of Mach number, static and stagnation pressure across a normal shock
- bThe 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
- cPropulsive efficiency
- aDiscuss 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
- bProve that when the Rayleigh flow is subsonic (Ma<1), fluid heating ( δq>0) increases fluid velocity while fluid cooling decreases fluid velocity
- aAir (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
- 1stagnation temperature
- 4area of the cross-section at exit
- bDiscuss what is meant by thrust augmentation and explain how it is affected 10
- aDiscuss the working of basic components of aircraft gas turbine engines. Also draw T-S diagram of Brayton cycle
- bA 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
- aPropulsion efficiency and propulsion power
- bEngine output and thermal efficiency, and
Question text is extracted from the official AKTU question paper PDF above. Hindi translations are omitted — every question is printed in English in the original paper. Last verified: 2026-08-23.
Repeated Questions — KME064
Questions that appeared in more than one session, found by comparing 2 years of Gas Dynamics And Jet Propulsion papers (2021-22, 2023-24)
Propulsive efficiency
Appeared in: 2021-22 · 2023-24
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