The material is only for academic purpose and for preparation of exams. Contents are copied from reference books. Not for revenue generation of any kind.
A presentation taking the student through how a Jet Engine works, and the different types of Jet Engine available. Initially written to prepare Air Cadets for their Jet Engine exam.
Pressure Distribution on an Airfoil
The team conducted the experiment to determine the effects of pressure distribution on lift and pitching moment and the behavior of stall for laminar and turbulent boundary layers in the USNA Closed-Circuit Wing Tunnel (CCWT) with an NACA 65-012 airfoil at a Reynolds number of 1,000,000. The airfoil was tested in a clean configuration at angles of attack of 0, 5, 8, 10, and 12 degrees. Tape added to the leading edge tripped the boundary layer, and pressure distributions were taken at 8, 10, and 12 degrees angle of attack. Experimental results showed a suction peak at less than 1% of chord, providing a beneficial test article for contrast between smooth and laminar boundary layer behavior at the stall condition. The maximum lift coefficient for the clean airfoil was 0.9 at 10 degrees angle of attack, and tripped airfoil reached a maximum lift coefficient of 1.03 at 12 degrees angle of attack, a 14% increase. These data were 10% lower than the empirical airfoil data found in Theory of Wing Sections from Abbott and von Doenhoff. Pitching moment coefficient about the quarter chord remained near zero below stall as expected for a symmetrical airfoil, but rapidly became negative after stall for experimental and empirical data. The airfoil exhibited a leading edge stall for both laminar and turbulent boundary layers.
This so called PPT for propulsion study for Shenyang Aerospace University. This PPT right protected by Dr. divinder K. Yadav. Its using in SAU by Lale. For all students of Aeronautical Engineering must memorize each & every words from this PPT. If you miss a single words you must fail in the Exam. Remember there is no chance to be creative or use sense you just need to use the power of memorizing.
SAIF ALDIN ALI MADIN
سيف الدين علي ماضي
S96aif@gmail.com
Presentation
on
Axial Flow Compressor
Introduction
Construction
Working
Design
Main Parts
Stalling
Surging
Stage Losses
Advantages - Disadvantages & Applications
A presentation taking the student through how a Jet Engine works, and the different types of Jet Engine available. Initially written to prepare Air Cadets for their Jet Engine exam.
Pressure Distribution on an Airfoil
The team conducted the experiment to determine the effects of pressure distribution on lift and pitching moment and the behavior of stall for laminar and turbulent boundary layers in the USNA Closed-Circuit Wing Tunnel (CCWT) with an NACA 65-012 airfoil at a Reynolds number of 1,000,000. The airfoil was tested in a clean configuration at angles of attack of 0, 5, 8, 10, and 12 degrees. Tape added to the leading edge tripped the boundary layer, and pressure distributions were taken at 8, 10, and 12 degrees angle of attack. Experimental results showed a suction peak at less than 1% of chord, providing a beneficial test article for contrast between smooth and laminar boundary layer behavior at the stall condition. The maximum lift coefficient for the clean airfoil was 0.9 at 10 degrees angle of attack, and tripped airfoil reached a maximum lift coefficient of 1.03 at 12 degrees angle of attack, a 14% increase. These data were 10% lower than the empirical airfoil data found in Theory of Wing Sections from Abbott and von Doenhoff. Pitching moment coefficient about the quarter chord remained near zero below stall as expected for a symmetrical airfoil, but rapidly became negative after stall for experimental and empirical data. The airfoil exhibited a leading edge stall for both laminar and turbulent boundary layers.
This so called PPT for propulsion study for Shenyang Aerospace University. This PPT right protected by Dr. divinder K. Yadav. Its using in SAU by Lale. For all students of Aeronautical Engineering must memorize each & every words from this PPT. If you miss a single words you must fail in the Exam. Remember there is no chance to be creative or use sense you just need to use the power of memorizing.
SAIF ALDIN ALI MADIN
سيف الدين علي ماضي
S96aif@gmail.com
Presentation
on
Axial Flow Compressor
Introduction
Construction
Working
Design
Main Parts
Stalling
Surging
Stage Losses
Advantages - Disadvantages & Applications
RAMJET is a type of jet engine in which the air drawn in for combustion is compressed solely by the forward motion of the aircraft.
A ramjet uses this high pressure in front of the engine to force air through the tube, where it is heated by combusting some of it with fuel.
It is then passed through a nozzle to accelerate it to supersonic speeds. This acceleration gives the ramjet forward thrust.
The turbofan engine is a propulsive mechanism to combine the high thrust of a turbojet with the high efficiency of a propeller. Basically, a turbojet engine forms the core of the turbofan; the core contains the diffuser, compressor, burner, turbine, and nozzle. However, in the
turbofan engine, the turbine drives not only the compressor, but also a large fan external to the core. The fan itself is contained in a shroud that is wrapped around the core.
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
This Presentation gives a brief idea on turbojet engines, their components, working principle and also on the materials used in both the hot and cold sections of the engine, applications, etc..
A gas turbine, also called a combustion turbine, is a type of internal combustion engine. It has an upstream rotating compressor coupled toa downstream turbine, and a combustion chamber in-between. Energy is added to the gas stream in the combustor, where fuel is mixed with air and ignited. In the high-pressure environment of the combustor, combustion of the fuel increases the temperature. The products of the combustion are forced into the turbine section
Visit https://www.topicsforseminar.com to Download
RAMJET is a type of jet engine in which the air drawn in for combustion is compressed solely by the forward motion of the aircraft.
A ramjet uses this high pressure in front of the engine to force air through the tube, where it is heated by combusting some of it with fuel.
It is then passed through a nozzle to accelerate it to supersonic speeds. This acceleration gives the ramjet forward thrust.
The turbofan engine is a propulsive mechanism to combine the high thrust of a turbojet with the high efficiency of a propeller. Basically, a turbojet engine forms the core of the turbofan; the core contains the diffuser, compressor, burner, turbine, and nozzle. However, in the
turbofan engine, the turbine drives not only the compressor, but also a large fan external to the core. The fan itself is contained in a shroud that is wrapped around the core.
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
This Presentation gives a brief idea on turbojet engines, their components, working principle and also on the materials used in both the hot and cold sections of the engine, applications, etc..
A gas turbine, also called a combustion turbine, is a type of internal combustion engine. It has an upstream rotating compressor coupled toa downstream turbine, and a combustion chamber in-between. Energy is added to the gas stream in the combustor, where fuel is mixed with air and ignited. In the high-pressure environment of the combustor, combustion of the fuel increases the temperature. The products of the combustion are forced into the turbine section
Visit https://www.topicsforseminar.com to Download
Design and Optimization of Valveless Pulsejet EngineIJERA Editor
Simple design and efficiency make pulsejet engines attractive for aeronautical short-term operation applications.
An active control system extends the operating range and reduces the fuel consumption considerably so that this
old technology might gain a new interest. During the operations of these pulsejet engines the surfaces of engine
will get more heated. In order to cool the engine surface and to get more thrust we have attached an additional
component called secondary inlet in that valve less pulsejet engine. The pulsejet is the only jet engine combustor
that shows a net pressure gain between the intake and the exhaust. The pulsejet is the only jet engine combustor
that shows a net pressure gain between the intake and the exhaust. We choose the LOCKWOOD’s design of
pulsejet engine. By using the CFD analysis we have analysed the modified design of valveless pulsejet engine.
This project provides an overview of this unique process and the results of these design modifications are
reported.
CFD Based Investigation on Effects of Compression Surface At Fighter Aircraft...IJERA Editor
The purpose of the intake of an aircraft is to supply the engine with a proper airflow during various flight conditions. A good intake design is characterized by providing high pressure recovery and low distortion. Therefore it is essential to divert as much of the boundary layer as possible since it is a factor which affect the quality of the airflow. On aircrafts with engines installed on wing pylons, which is the most common configuration on transport and passenger aircraft, the inlet is short and leads directly to the engine and the pressure recovery is good. For engines that are integrated with the body, for example on fighter aircrafts, the airflow is travelling along the body of the aircraft before it reaches the air intake. A boundary layer builds up along the body, something which is not desirable, especially in the part of the flow that supplies the engines. The pressure recovery is lower because of this, something that has a negative effect upon engine thrust. There are, however, ways to prevent the boundary layer from entering the inlet, or at least to minimize the amount that does. It is common to use a boundary layer diverter. It affects the aircraft performance in so many ways. So, it needs some other provision or technology to overcome intake problem in fighter crafts. In the present work, a well-designed compression surface is installed in the entry of the engine intake to redirect boundary layer and create shock wave for getting desired flow in the compressor (When a flow crosses a shock wave, its velocity got reduced, which in term increases pressure). The compression surface is placed at the entry of the diffuser to perform the above mentioned operation. The work extents to, a comparative investigation is proposed for with and without compression surface. ANSYS-Fluent is a commercial CFD code which will be used for performing the simulation and the simulation configuration contains two different Mach speeds (0.7 & 2) with three different angles of attacks (0°, 7.5° and 15°). The simulation results are evaluated to find out pressure recovery in the engine intake between with and without compression surface.
Rockets and missiles solved question bank - academic purpose onlySanjay Singh
The study material will be useful for aeronautical engineering students for preparation for their exams. It is made for academic purpose only and not for revenue generation of any kind. Rocket Propulsion Elements by Sutton is used for preparation of this QB.
Unit IV Solved Question Bank- Robotics EngineeringSanjay Singh
This Question Bank for Robotics Engineering is only for academic purpose and not for any commercial use. Students of Anna University and other Universities can use it for reference and knowledge.
Unit III - Solved Question Bank- Robotics Engineering -Sanjay Singh
This Question Bank for Robotics Engineering is only for academic purpose and not for any commercial use. Students of Anna University and other Universities can use it for reference and knowledge.
Unit v - Solved qb - Robotics EngineeringSanjay Singh
This Question Bank for Robotics Engineering is only for academic purpose and not for any commercial use. Students of Anna University and other Universities can use it for reference and knowledge.
Unit II Solved Question Bank - Robotics Engineering -Sanjay Singh
This Question Bank for Robotics Engineering is only for academic purpose and not for any commercial use. Students of Anna University and other Universities can use it for reference and knowledge.
Courier management system project report.pdfKamal Acharya
It is now-a-days very important for the people to send or receive articles like imported furniture, electronic items, gifts, business goods and the like. People depend vastly on different transport systems which mostly use the manual way of receiving and delivering the articles. There is no way to track the articles till they are received and there is no way to let the customer know what happened in transit, once he booked some articles. In such a situation, we need a system which completely computerizes the cargo activities including time to time tracking of the articles sent. This need is fulfilled by Courier Management System software which is online software for the cargo management people that enables them to receive the goods from a source and send them to a required destination and track their status from time to time.
About
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
• Remote control: Parallel or serial interface.
• Compatible with MAFI CCR system.
• Compatible with IDM8000 CCR.
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
• Easy in configuration using DIP switches.
Technical Specifications
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
Key Features
Indigenized remote control interface card suitable for MAFI system CCR equipment. Compatible for IDM8000 CCR. Backplane mounted serial and TCP/Ethernet communication module for CCR remote access. IDM 8000 CCR remote control on serial and TCP protocol.
• Remote control: Parallel or serial interface
• Compatible with MAFI CCR system
• Copatiable with IDM8000 CCR
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
Application
• Remote control: Parallel or serial interface.
• Compatible with MAFI CCR system.
• Compatible with IDM8000 CCR.
• Compatible with Backplane mount serial communication.
• Compatible with commercial and Defence aviation CCR system.
• Remote control system for accessing CCR and allied system over serial or TCP.
• Indigenized local Support/presence in India.
• Easy in configuration using DIP switches.
Automobile Management System Project Report.pdfKamal Acharya
The proposed project is developed to manage the automobile in the automobile dealer company. The main module in this project is login, automobile management, customer management, sales, complaints and reports. The first module is the login. The automobile showroom owner should login to the project for usage. The username and password are verified and if it is correct, next form opens. If the username and password are not correct, it shows the error message.
When a customer search for a automobile, if the automobile is available, they will be taken to a page that shows the details of the automobile including automobile name, automobile ID, quantity, price etc. “Automobile Management System” is useful for maintaining automobiles, customers effectively and hence helps for establishing good relation between customer and automobile organization. It contains various customized modules for effectively maintaining automobiles and stock information accurately and safely.
When the automobile is sold to the customer, stock will be reduced automatically. When a new purchase is made, stock will be increased automatically. While selecting automobiles for sale, the proposed software will automatically check for total number of available stock of that particular item, if the total stock of that particular item is less than 5, software will notify the user to purchase the particular item.
Also when the user tries to sale items which are not in stock, the system will prompt the user that the stock is not enough. Customers of this system can search for a automobile; can purchase a automobile easily by selecting fast. On the other hand the stock of automobiles can be maintained perfectly by the automobile shop manager overcoming the drawbacks of existing system.
Democratizing Fuzzing at Scale by Abhishek Aryaabh.arya
Presented at NUS: Fuzzing and Software Security Summer School 2024
This keynote talks about the democratization of fuzzing at scale, highlighting the collaboration between open source communities, academia, and industry to advance the field of fuzzing. It delves into the history of fuzzing, the development of scalable fuzzing platforms, and the empowerment of community-driven research. The talk will further discuss recent advancements leveraging AI/ML and offer insights into the future evolution of the fuzzing landscape.
COLLEGE BUS MANAGEMENT SYSTEM PROJECT REPORT.pdfKamal Acharya
The College Bus Management system is completely developed by Visual Basic .NET Version. The application is connect with most secured database language MS SQL Server. The application is develop by using best combination of front-end and back-end languages. The application is totally design like flat user interface. This flat user interface is more attractive user interface in 2017. The application is gives more important to the system functionality. The application is to manage the student’s details, driver’s details, bus details, bus route details, bus fees details and more. The application has only one unit for admin. The admin can manage the entire application. The admin can login into the application by using username and password of the admin. The application is develop for big and small colleges. It is more user friendly for non-computer person. Even they can easily learn how to manage the application within hours. The application is more secure by the admin. The system will give an effective output for the VB.Net and SQL Server given as input to the system. The compiled java program given as input to the system, after scanning the program will generate different reports. The application generates the report for users. The admin can view and download the report of the data. The application deliver the excel format reports. Because, excel formatted reports is very easy to understand the income and expense of the college bus. This application is mainly develop for windows operating system users. In 2017, 73% of people enterprises are using windows operating system. So the application will easily install for all the windows operating system users. The application-developed size is very low. The application consumes very low space in disk. Therefore, the user can allocate very minimum local disk space for this application.
CFD Simulation of By-pass Flow in a HRSG module by R&R Consult.pptxR&R Consult
CFD analysis is incredibly effective at solving mysteries and improving the performance of complex systems!
Here's a great example: At a large natural gas-fired power plant, where they use waste heat to generate steam and energy, they were puzzled that their boiler wasn't producing as much steam as expected.
R&R and Tetra Engineering Group Inc. were asked to solve the issue with reduced steam production.
An inspection had shown that a significant amount of hot flue gas was bypassing the boiler tubes, where the heat was supposed to be transferred.
R&R Consult conducted a CFD analysis, which revealed that 6.3% of the flue gas was bypassing the boiler tubes without transferring heat. The analysis also showed that the flue gas was instead being directed along the sides of the boiler and between the modules that were supposed to capture the heat. This was the cause of the reduced performance.
Based on our results, Tetra Engineering installed covering plates to reduce the bypass flow. This improved the boiler's performance and increased electricity production.
It is always satisfying when we can help solve complex challenges like this. Do your systems also need a check-up or optimization? Give us a call!
Work done in cooperation with James Malloy and David Moelling from Tetra Engineering.
More examples of our work https://www.r-r-consult.dk/en/cases-en/
Event Management System Vb Net Project Report.pdfKamal Acharya
In present era, the scopes of information technology growing with a very fast .We do not see any are untouched from this industry. The scope of information technology has become wider includes: Business and industry. Household Business, Communication, Education, Entertainment, Science, Medicine, Engineering, Distance Learning, Weather Forecasting. Carrier Searching and so on.
My project named “Event Management System” is software that store and maintained all events coordinated in college. It also helpful to print related reports. My project will help to record the events coordinated by faculties with their Name, Event subject, date & details in an efficient & effective ways.
In my system we have to make a system by which a user can record all events coordinated by a particular faculty. In our proposed system some more featured are added which differs it from the existing system such as security.
Cosmetic shop management system project report.pdfKamal Acharya
Buying new cosmetic products is difficult. It can even be scary for those who have sensitive skin and are prone to skin trouble. The information needed to alleviate this problem is on the back of each product, but it's thought to interpret those ingredient lists unless you have a background in chemistry.
Instead of buying and hoping for the best, we can use data science to help us predict which products may be good fits for us. It includes various function programs to do the above mentioned tasks.
Data file handling has been effectively used in the program.
The automated cosmetic shop management system should deal with the automation of general workflow and administration process of the shop. The main processes of the system focus on customer's request where the system is able to search the most appropriate products and deliver it to the customers. It should help the employees to quickly identify the list of cosmetic product that have reached the minimum quantity and also keep a track of expired date for each cosmetic product. It should help the employees to find the rack number in which the product is placed.It is also Faster and more efficient way.
Planning Of Procurement o different goods and services
Proulsion I - SOLVED QUESTION BANK - RAMJET ENGINE
1. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
UNIT V (RAMJET PROPULSION)
PART A (Short Answer Questions)
1. How can you define a ramjet engine?
Ans. Ramjet engine is mechanically the least complicated air-breathing jet engine for thrust production
for flying vehicles. It does not have any rotating components like compressor and turbine. Necessary
pressure rise takes place solely due to design of supersonic air intake and shock waves.
2. State the operating principle of a ramjet engine.
Ans. The ramjet engine produces power by increasing the momentum of the working fluid by induction of
energy by combustion of fuel, so that the momentum of the exhaust jet exceeds that of the incoming air,
on a continuous basis. In contrast to the other air-breathing engines, the working cycle is accomplished
without additional components of compression and expansion, and also without any need for enclosed
combustion.
3. Draw a neat and labeled diagram of ramjet engine.
Ans.
4. Name the various components of a ramjet engine.
Ans. Diffuser, Burner and Nozzle.
5. Differentiate between ramjet and scramjet engine.
Ans. A ramjet is an air breathing jet engine in which combustion takes place in subsonic airflow.
A scramjet is a variant of a ramjet air breathing jet engine in which combustion takes place in
supersonic airflow.
6. State the advantages and disadvantages of ramjet.
Ans. Advantages: i) Ramjet engine is very simple and does not have any moving part.
ii) Cost is low.
2. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
iii) Less maintenance.
iv) There is no upper limit for flight speed.
v) Light weight compared to turbojet engine.
Disadvantages : i) Since the take off thrust is zero, it is not possible to start a ramjet engine without an
external launching device.
ii) The combustor required flame holder to stabilize the combustion due to high speed
of air.
iii) It has low thermal efficiency.
iv) It is very difficult to design a diffuser which will give good pressure recovery over a
wide range of speeds.
7. Differentiate between subsonic and supersonic inlets.
Ans. Inlets are broadly divided into subsonic and supersonic, depending upon the flight Mach number of
the vehicle. They may be further subdivided into external compression inlets in which the flow
compression takes place in the free stream and internal compression inlets wherein the flow compression
takes place inside of the inlet flow passage.
8. Name the modes of operation of operation of a supersonic inlet.
Ans. Critical, Subcritical and Supercritical modes in which a supersonic inlet works.
9. What do you mean by shock swallowing?
Ans. Shock swallowing is the condition of supersonic inlet in which shock waves moves inside the
diffuser section and thereby high deceleration takes place consequent to high pressure rise.
10. What is the purpose of flame holders in ramjet combustors?
Ans. The purpose of flame holders in ramjet combustors is to stabilize the flame and prevent extinguishing
of the flame inside the combustion chamber for a continuous combustion.
11. What is called a shock wave?
Ans. A shock wave is a special kind of pressure wave with a steep pressure rise. It may also be described
as a compression wave front in a supersonic flow field and the flow across the wave front results in abrupt
change of fluid properties.
12. Differentiate between normal and oblique shock.
Ans. When the shock wave gets positioned at right angle to the flow direction, it is known as a normal
shock wave and when the shock wave gets positioned at an angle to the flow direction other than right
angle, it is known as an oblique shock wave.
13. What is the operating cycle of a ramjet engine?
Ans. The operating cycle of a ramjet engine is similar to turbojet engine except that the complete
compression of the intake air is achieved by the ram effect of the inlet diffuser, thus avoiding the
3. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
mechanical compressor. Since the compressor is eliminated, its prime mover, the turbine is also
eliminated.
14. State the purpose of a diffuser.
Ans. The purpose of a diffuser is to decelerate the flow thereby an increase in pressure due to ram effect.
15. How does the ramjet engine produce power?
Ans. The air is diffused to sufficiently low velocity so that it is possible to add the required heat in the
combustion chamber and thereby produce power by expanding the hot exhaust gases through nozzle for
production of thrust power.
16. Ramjet engine is mechanically the least complicated air-breathing jet engine for thrust production in
flying vehicles. Justify
Ans. Since the rotating components are eliminated in ramjet engines, it consists of only three major
components – Diffuser, Burner and nozzle. Hence, Ramjet engine is mechanically the least complicated
air-breathing jet engine for thrust production in flying vehicles.
17. What does it happen when air is decelerated from high Mach number to a low subsonic Mach number?
Ans. When air is decelerated from high Mach number to a low subsonic Mach number, it causes a
pressure rise ratio of even more than 34.
18. Draw T-s diagram of an ideal ramjet cycle.
Ans.
19. Write the energy balance equation across a ramjet combustor.
4. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
Ans.
20. What do you mean by thrust specific fuel consumption?
Ans.
The specific fuel consumption used in a jet engine is the Thrust Specific Fuel Consumption (TSFC), since
the output of a jet engine is in the form of thrust.
PART B (Long Answer Questions)
1. Describe construction, principle and operation of a ramjet engine with a neat diagram showing various
components.
Ans. Ramjet engines consist of intakes, combustors and nozzles. The entire compression process is
accomplished in the intake of the ramjet. Intakes therefore form a very important component of ramjets.
After the intake, the compressed air goes into the combustor. The combustion products are then expanded
through the nozzle to generate thrust.
Ramjet intakes are usually of the supersonic, variable ramp geometry. The ramp position will be
adjusted depending upon the operating condition. The intake usually employs 2-3 oblique shocks followed
by a normal shock for decelerating the flow. After the normal shock, the flow that is subsonic is further
decelerated using a diffuser.
Unlike other jet engines like turbojets, turbofans etc, there are no rotating components in ramjets. The
temperatures in the combustion chamber are therefore much higher than the conventional jet engines.
Maximum temperatures as high as 3000K are common in ramjets. Ramjet combustors are similar to the
afterburners used in turbojet engines.
5. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
Combustors have flame holders for stabilizing the flame within the combustor. The length of the
combustor depends upon the fuel used, the injector characteristics and the flame holders. Though flame
holders are essential to ensure stable combustion, they also lead to total pressure losses. Designers would
need to optimize the blockage due to flame holders.
A discussion of a ramjet engine can be simplified by assuming that the ramjet is stationary, and that air
approaches the engine at a velocity equal to the vehicle speed. As air enters the inlet, adiabatic
compression causes an increase in temperature and a decrease in velocity. The air is further heated by
combustion of the fuel which also increases the mass flow, typically between 5 and 10%. The high-
temperature compressed gases then are expanded in the nozzle and accelerated to high velocity. The thrust
developed by the engine is the net rate of change of momentum of the gases passing through the engine
and is equal to the mass flow rate of the air plus burned fuel times the jet velocity minus the flow rate of
air times the air velocity. The effective net thrust on the vehicle will be somewhat less than the engine
thrust because of skin friction drag on the air flowing around the ramjet vehicle.
6. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
2. Explain how moving parts are eliminated in a ramjet engine. In what way it is different from a
scramjet engine?
8. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
3. A ramjet engine is designed to operate at a Mach number of 2 to 8 km altitude. A divergent conical
inlet diffuser is employed and is designed such that a normal shock is formed at the entrance of the
diffuser and the Mach number at the exit of the diffuser is 0.2. Heat added in the combustion chamber
is such that the total temperature of the gases at inlet to the choked nozzle is 2000 K. Find the area
9. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
ratio required for the diffuser. Also find out the heat to be added in the combustion chamber per kg of
gas flow through the nozzle and the Mach number at the inlet to the nozzle. Assume that the internal
flow id frictionless.
Ans.
4. Briefly explain the working of a pulsejet engine. In what way it is different from a ramjet engine?
Ans.
10. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
5. “The ramjets engines are more suitable for supersonic flight.” Substantiate the statement. Explain why
ramjet engines are not that suitable for hypersonic flights.
Ans.
6. A ramjet is flying at Mach 1.818 at an altitude 16.750 km altitude (Pa = 9.122 kPa, Ta= -56.50
C =
216.5 K., sonic speed, a = 295 m/s). The flow is assumed to enter the intake of the ramjet through a
normal shock standing at the intake face. No pre-entry loss or friction loss inside the engine is
assumed to exist. Combustion delivery temperature is 1280 K and the fuel –air ratio is 1:40. The area
at the intake face is A1= 0.0929 m2
and at the Combustion chamber, A3= 0.1858 m2.
Calculate : (a) Mass flow rate through the engine (b) Throat area in the nozzle, A5
(c) Combustion related pressure drop in the combustion chamber
(d) If the nozzle expands to ambient pressure –find the thrust produced
(e) If the nozzle expands only in a convergent nozzle –find the thrust produced
(f) Calculate the propulsive efficiencies for (d) and (e)
(g) Calculate TSFC in both the cases
(h) Complete and draw the cycles for the cases –(i) with C-D nozzle and
(ii) Convergent nozzle
7. Explain difference between subsonic and supersonic inlets. Also describe modes of operation of
supersonic inlets with neat diagrams.
15. VMKV ENGINEERING COLLEGE
DEPARTMENT OF AERONAUTICAL ENGINEERING
QUESTION BANK – IV SEMESTER – REGULATION 2015
SUBJECT - PROPULSION - I
8. Describe the working of a ramjet engine. Depict various thermodynamic processes occurring on h-s
diagram.
Ans. Refer Q. No. 1 and 2 of Part B.
9. Explain ram effect. Explain how ram effect is achieved in turbojet and ramjet engines.
Ans. Refer Q. No. 1 and 2 of Part B.
10. A 0.5 m diameter ramjet engine having a diverging conical inlet diffuser and a converging exhaust
nozzle is designed to operate at a flight Mach number 1.7 at 8 km altitude. The total temperature of
gases at entrance to the exhaust nozzle is 2000 K. The fuel has a heating value of 45 MJ/Kg. Assuming
that there is no pressure loss, that the air enters the combustion chamber with a Mach number 0.2, that
at the design condition a normal shock forms at the entrance to the diffuser and that the nozzle is
choked, calculate (i) cross-sectional area at the exit of the diffuser (ii) exit area of the nozzle (iii) mass
flow rate of air (iv) fuel air ratio (v) loss in total pressure (vi) effective jet velocity (vii) thrust. Neglect
the variation of γ and Cp.