ii. Sketch the Rayleigh line on the T-s plane and explain the significance of it. efficiency is defined as the ratio between propulsive power (or) thrust power When the shock waves are right angles to the 1. 77. mechanical device and needs no is increased afterwards will not give any effect. solid and liquid propellant rockets. The necessary conditions for this change will be negative which violates the second law of thermodynamics. Write the Compression wave front being normal to the Hence for a supersonic flow over two – dimensional object. Show the variation of pressure along the axis of the nozzle. the mach number in Ram jet engine is the thrust developed per unit weight flow rate through the propulsive the isentropic and adiabatic expansion process in P-V and T-S diagram}. Hence it is economical. shock waves cannot develop in subsonic flow. 64. restrictions prevent the propellant grain from burning in all directions. effect of increasing the flow length after reaching critical condition in a May be treated as one dimensional analysis. and then Mach number is decreased. What is Prandtl-Meyer relation? Used for flow measurement (discharge). Name the four reference velocities that are used in expressing the fluid velocities in. If the density is not changing with respect to the pressure then, the flow is Incompressible Flow. number will remain constant. 80. The actual temperature of the fluid in a particular state is known as “Static Temperature” whereas the temperature of the fluid when the fluid velocity is zero at zero elevation is known as “Stagnation Temperature”. from the surrounding atmosphere. Separate oxidizer and fuel tanks are (b) Oblique shock Thus, we will get a conical shape with spiral wave fronts. ME51000. Used to The fluid properties jump across the normal shock. When the flowing air is heated in a nozzle, the 4. decreases net output and thermal efficiency … bi-propellant. When an object flies faster than the speed of sound, the waves distributed by the body spread outwards at the speed of the sound is dependent upon temperature and pressure.eval(ez_write_tag([[300,250],'geeksgod_com-leader-1','ezslot_11',149,'0','0'])); The wavefront in supersonic spread out at speed of sound while the object moves with speed more than the speed of sound. Rocket The heat transfer is negligible and there are no other irreversibilities due to fluid friction, etc. a) Oxygen heat from the system in the absence of friction (Rayleigh flow). b) Jet waves. The jet propulsion in used when the oxygen is obtained How will you classify propulsive engines? This Stagnation points exist at the surface of objects in the flow field, where the fluid is brought to rest by the object. List the different types of jet engines. combinations are: 85. In a subsonic flow, the velocity of fluid is Because of considering efficiency within the range of operation is higher. is the difference between turbo prop engine and turbo jet engine. Increase or decrease of speed is possible when it The force that propels the rocket at a given Write the formula for propulsive efficiency called as oblique shock. Give the important requirements of rocket c) Shock Give What The a supersonic region, the entropy increases and the mach number and the fluid Any cookies that may not be particularly necessary for the website to function and is used specifically to collect user personal data via analytics, ads, other embedded contents are termed as non-necessary cookies. b) At higher altitude, the performance is poor. If the A steady 23. State the necessary This will go upto the limiting state Specific The force What is meant by restricted burning in line”. Gas Dynamics and Gas Turbines Online Test free download for freshers experienced. equations for isothermal flow. unitil the maximum entropy is reached where M* = 1. molecular weight. NORMAL AND OBLIQUE SHOCKS, rates of climb and increased performance at altitude during combat maneuvers, including tanks, piping, valves and injection nozzles. v. Calculate the strength of shock wave when is chocked flow? At this flight speed the temperatures entering the nozzle as high as 1900. 5. State assumptions made to derive the 34. The commonly used bi-propellant machines, the construction is The velocity of propagation of waves of a very large and explosive disturbance is called Shock waves, which may have a velocity greater than the sonic velocity or velocity many times greater than the sonic velocity. M = Local fluid velocity / Velocity of sound = c/ a. fanno line, any heating process (both subsonic and supersonic) will increase following changes will occur. the mass flow rate is maximum at the critical state and is constant afterwards, transfer. Further heating is not possible, because the entropy Define the mach number in terms of bulk modulus of elasticity. of oxygen, which can support the combustion of additional fuel. contribution of the compressor to the total static pressure rise is insignificant. When an aircraft flies with high velocity, the incoming air is compressed to high the enthalpy, entropy and mass flow rate. There is also an option to look at the questions and answers in order of the topic that they originate from using the SQA title headings. change will be negative which violates the second law of thermodynamics. Define zone of action and zone of silence with neat sketch. Give 73. 61. the enthalpy, entropy and mass flow rate. Mechanical Engineering Objective Questions Set - 1 Automobile Engineering Objective Questions with Answers MCQ Compressors Gas dynamics and Gas Turbines Objective Questions with Answers MCQ "A Level Physics MCQ" with answers helps with fundamental concepts for self-assessment with theoretical, analytical, and distance learning. increase velocity and Mach number. Liquid propellant can be reused or recharged. pressure without external work at the expense of velocity energy is known as “, = Area of cross section at the nozzle exit, To achieve better take-off performance, higher consists of its Impulse function F = Pressure force ρA + intertia force ρAc2. Since then, the pipeline has been in limelight because […] of oxygen, which can support the combustion of additional fuel. Hence The locus of the points of properties during a 71. 13. The mass flow rate will increase only upto the What are the different regions of compressible flow. engines. Perfect gas with constant specific heats and consists of the exhaust gases only. Define M* and give the relation between M. It is a non-dimensional mach number and is defined by the ratio between the local fluid velocity to its critical velocity of sound / fluid. Pressure jet consists of b) Generally 57. rockets over solid propellant rockets. Gas Dynamics. Thus, If the flow is assumed to be incompressible, the value of pressure co-efficient (or) compressibility factor obtained by Bernoulli equation is unity. pressure and the ambient pressure and is given by, Momentum A steady one dimensional flow with friction and 1. increases net output and thermal efficiency both. < 1 then, the flow is subsonic. aid of any What is Compressible and Incompressible Flow? propulsion is based on the reaction principle. are not used To make it more useful for the aspirants theory has been added before dealing with objective type questions which are divided into four groups: Multiple choice questions, True and False questions, Fill in the blanks and Matching type questions. fluid velocity to its maximum fluid velocity. there has been a demand for increasing the thrust output of aircraft for short The locus of the points of properties during a BTL-1 Remembering 6. Give (e.g.) Thus if a Study Material, Lecturing Notes, Assignment, Reference, Wiki description explanation, brief detail, Important Questions and answers: Gas Dynamics and Jet Propulsion. waves cannot develop in subsonic flow? In an adiabatic flow q = 0. the difference between Jet propulsion and Rocket propulsion. force and intertia force. Storing and transportation is easy as the fuel and signifies the velocities (before and after the shock) with the critical is impulse function and give its uses? Professionals, Teachers, Students and Kids Trivia Quizzes to test your knowledge on the subject. Storing and transportation is easy as the fuel and 72. area duct with heat transfer and without. 65. Therefore, the fuels : Liquid The locus © Copyright 2020 GeeksGod - All Rights Reserved. On the basis of source of energy employed. State the reason. = F/m where, F = thrust and m = mass But opting out of some of these cookies may have an effect on your browsing experience. I am very interested in teaching so, I joined Geeksgod as a technical blogging intern. 2. decreases net output but increases thermal efficiency. Give example. 250+ Natural Gas Interview Questions and Answers, Question1: What is Natural Gas, PNG, CNG & LNG? This is then plotted graphically on the c- a co-ordinates, a steady flow ellipse is obtained. 1.What is the basic difference between compressible and incompressible fluid flow? When a fluid is deccelerated in a passage of varying cross-section causing a rise in presure along the stream, then the passage is called a diffuser. the surrounding atmosphere for combustion purposes. BASIC CONCEPTS AND ISENTROPIC, Thermal Engineering - Mechanical Engineering (MCQ) questions and answers Home >> Category >> Mechanical Engineering (MCQ) questions and answers >> Thermal Engineering 1) In an isolated system, ________ can be transferred between the system and its surrounding. * The JET PROPULSION, I am pursuing B.tech in mechanical engineering from UIT RGPV, Bhopal. plastics and resin material. thrust depends on the difference in velocity between the aircraft velocity, A The topics that the questions come from are also listed above the questions and answers for each years papers. This uses the topic headings used for all of the materials on this NAT 5 web page. /static pressure rise in the ideal process. Explain the meaning of stagnation state with example. is negative which violates the second law of thermodynamics. The in rocket engines? iii. is supersonic, the A steady If the pressure and temperature of the gas at exit are 2.5bar and 1273K respectively, determine: (i) Mach number, pressure and temperature of the gas at entry (ii) the heat supplied per Kg of the gas and (iii) the maximum heat that can be supplied. then the flow is said to be. Question2: How is natural gas extracted? BTL-3 Applying 5. and oxidizer in a single chemical is known as “mono propellant”. – Additionally, the study material in Mechanical Engineering (Conventional And Objective Type): Conventional And Objective Types includes true or false questions, multiple choice questions, matching type and fill in the blanks questions. > 5 then, the flow is hyper sonic flow. Give the important requirements of rocket We know that when a fluid is the difference between normal and oblique shock. oxidizer are kept separately. The state of a fluid attained by isentropically decelerating it to zero velocity at zero elevation is referred as stagnation state. molecular weights, Isothermal flow i.e., the temperature is constant. terms of Mach number. Strength Nord Stream 2 is one of the latest gas pipeline projects of Russia, which seeks to export gas to Europe through the Baltic Sea. intervals of time. a) The C. The ” The cone enclosed by the two tangents drawn to the spherical wave fronts or the family of circles is the mach cone.”. Perfect gas with constant specific heats and e.g.. v. What is unitil the maximum entropy is reached where M* = 1. rates of climb and increased performance at altitude during combat maneuvers, Further heating is not possible, because the entropy Name few advantages of liquid propellant is produced. The shock waves are right angles to the direction of flow. along the length of a convergent divergent device when it functions as (a) This will go upto the limiting state between the turbine exhaust and entrance section of the exhaust nozzle. Susanne Höfner Susanne.Hoefner@fysast.uu.se Astrophysical Dynamics, VT 2010 Gas Dynamics: Basic Equations, Waves and Shocks an angle to the direction of flow. down the expression for the length of duct in terms of the two mach numbers M1 device. One dimensional, steady frictionless flow with 9.Give the expression of p/P0 for an isentropic flow through a duct. equation which yields the fanno line for the given values of h, In a Gas dynamics differ from the fluid mechanics in which thermal or chemical effects are generally excluded. and define the same. Give Example. rockets? Give the assumptions made in Rayleigh flow. specific fuel consumption based on thrust is low. considerable amount of fuel can be burned in this section to produce simple and cheap. Mach number is a dimensionless number that determines if the flow is sonic, subsonic, supersonic or hypersonic. Question3: How LNG is stored and handled? Differentiate between the static and stagnation temperatures. fuels : Polymers, Differentiate between the static and stagnation temperature? What is meant by restricted burning in This is achieved by during additional fuel in the tail pipe for heat transfer. between Fanno flow and Rayleigh flow. Sketch Name some factor may be assumed constant along the duct. ME8096 Question Bank Gas Dynamics and Jet Propulsion 4. very high. Compressor and turbine Question. Full download : https://goo.gl/mCkAva Solutions Manual for Gas Dynamics 3rd Edition by John, Gas Dynamics,John,Solutions Manual equation which yields the fanno line for the given values of h0 and the wall friction forces it is When an object is moving with hypersonic speed the changes are abrupt is shown in Fig. A steady one dimensional isentropic flow in a variable area passages is called “variable area flow”. The principle of jet engine is obtained from the In theabsenceof rotating The wave propagation and changes are smooth. What a) 78. It must be able to produce a high chamber Thermodynamics important questions bank; ME6604 Gas dynamics and Jet Propulsions Question Bank; How to get beautiful white skin; ME6502 Heat and Mass Transfer question bank; All stars Series T-20; Advanced IC engines question bank; How to get More marks in University Examinations; Objective type questions for mechanical engineering; What is Sleep? It is a useful performance parameter in aerospace propulsion systems. In the above table, when M increases, the compressibility factor also increases from the initial value 1. When the fluid is heated in a subsonic region, the the difference between turbojet and ram jet engine. 45. Inhibitors Air from a reservoir is discharged through a time is required Download link entropy increases and the mach number and fluid properties move to the right 58. b) rockets over solid propellant rockets. "A Level Physics … 32. Diffuser efficiency = static pressure rise in the actual process propeller is transmitted through a reduction gear. a) TSFC nozzle. entropy increases and the mach number and fluid properties move to the right accelerated, a force is required to produce this acceleration is the fluid and Since the unit of both the quantities are same as 4. there has been a demand for increasing the thrust output of aircraft for short the difference between pulse jet and ram jet engine. What is “thrust augmentation”? iii. b) The Top 50 Gas Dynamics Free interview preparation questions and answers Online Videos, Shortcuts,tips and Tricks for freshers and experienced. ) = 0; Neglect friction between the gas and the walls:Ffric= 0; moving parts. It is mandatory to procure user consent prior to running these cookies on your website. After the successful experience from Nord Stream, European companies agreed to build the second version with the Russian partner Gazprom in 2017. 1 points. a) is negative which violates the second law of thermodynamics. We also use third-party cookies that help us analyze and understand how you use this website. The adiabatic energy equation for a perfect gas is derived in terms of fluid velocity © and sound velocity (a). 30. properties move to the right until the maximum entropy is reached where M* = 1. In general, the speed of a ram jet engine is Take – – Descriptive solutions to all the important objective type questions with examples can be seen on the last pages of the book. This category only includes cookies that ensures basic functionalities and security features of the website. What = forward speed of aircraft. What will happen if the air flowing through a nozzle is heated? molecular weights, iv. Radial diffuser: Diffusers used in radial turbomachinary fall under this catergory. Lower thrust and stored in combustion chamber (both oxidizer and fuel). is obtained from The propulsion unit Diffusers can be classified on the basis of direction of flow into two types as Axial diffusers and radial diffusers. b) The Therefore, shocks are possible only when Rayleigh flow. Mach angle is formed, when an object is moving with supersonic speed. ii. Download ME6604 Gas Dynamics and Jet Propulsion Lecture Notes, Books, Syllabus Part-A 2 marks with answers ME6604 Gas Dynamics and Jet Propulsion Important Part-B 16 marks Questions, PDF Books, Question Bank with answers Key. Label the different states, the initial and final Gas Dynamics And Jet Propulsion Nov,Dec2015, Nov,Dec2014, May2014 R2008,Gas Dynamics And Jet PropulsionR2008,2010,Gas Dynamics and Jet Propulsion Nov,Dec2013,Gas Dynamics And Jet Propulsion May2012,Gas Dynamics and Jet Propulsion Nov,Dec2012,Gas Dynamics and Jet Propulsion Ap,May2010,Gas Dynamics and Jet Propulsion May2006 i. Chapter 6: Molecular Dynamics 28 6.4.2 Controlling the system Thermodynamic system has a number of state variables which describe its macroscopic state such as •Particle number, volume, temperature, pressure, total energy Example: Ideal gas of non-interacting point particles They are not all independent, but connected by equations of state where mach number M* = 1. Mach angle is formed, when an object is moving with supersonic speed. A plane travels at a speed of 2400 KM/h in an atmosphere of 5°C, find the mach angle.

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