Exam Details
| Subject | Aerodynamics- II | |
| Paper | ||
| Exam / Course | B.Tech in Aerospace Engineering (BTAE) | |
| Department | School of Engineering & Technology (SOET) | |
| Organization | indira gandhi national open university | |
| Position | ||
| Exam Date | December, 2016 | |
| City, State | new delhi, |
Question Paper
No. of Printed Pages 4 IBAS-015 I
B.Tech. AEROSPACE ENGINEERING
(BTAE)
Term-End Examination
December, 2016
BAS-O15 AERODYNAMICS -II
Time: 3 hours Maximum Marks: 70
Note: Answer any seven questions. Use of scientific calculator is permitted.
1. Explain the procedure to obtain supersonic nozzle contour for a given Mach number using method of characteristics. 5
An incident shock wave angle of 35 degrees impinges on a straight wall. If the upstream flow properties are M P 1 atm and T =300 calculate the reflected shock wave angle with respect to the wall and the flow properties P and T downstream of the reflected shock wave. 5
2. Differentiate between nozzle and venturi. State the necessary conditions for a choked flow to occur in a nozzle. 5
A diffuser has exit throat area ratio of 1.5 to 1. The inlet Mach number is 0·8. The initial pressure and temperature are 1 bar and 15°C. Assuming the flow to be isentropic, calculate the following for air: 5
Exit pressure
Exit temperature
Exit Mach number
3. Derive the energy equation for one-dimensional steady compressible flow from first principle. Deduce the isentropic relation between stagnation and sonic conditions for temperature, pressure and density. 6
Sketch the shock polar for M 2·5 and explain the method of finding the Mach numbers and shock angles for a turning angle of 5 degrees. 4
4. Answer any four of the following questions in brief: 4 x 2 1/2 =10
What is displacement thickness?
State the limitations of lifting line theory.
Explain the assumption of horse-shoe vortex.
What is boundary layer?
Define centre of pressure.
What is shock polar?
5. Derive the relation between Mach number and flow properties, viz., pressure, temperature and density across a normal shock wave. 5
State and explain the expression for linearized supersonic pressure coefficient. What are the assumptions made Enumerate. 5
6. Derive the relationship between the ratio of stagnation pressure to static pressure and Mach number for an isentropic flow. Derive the similar relations for temperature and density ratios. 6
A wedge of variable half angle is kept in a supersonic stream of Mach 2. Determine the maximum half angle up to which attached shock is possible. 4
7. What is the principle of operation of a typical shock tunnel? For an oblique shock wave, derive the relationships between the flow parameters in front of the shock and behind the shock. 10
8. Differentiate between static and stagnation temperatures. 5
Calculate the velocity of sound and the stagnation temperature of a jet at 300 K. Assume Mach number of 1.2. 5
9. Derive an expression for velocity of sound in air and show that it is proportional to the square root of absolute temperature of air. 10
B.Tech. AEROSPACE ENGINEERING
(BTAE)
Term-End Examination
December, 2016
BAS-O15 AERODYNAMICS -II
Time: 3 hours Maximum Marks: 70
Note: Answer any seven questions. Use of scientific calculator is permitted.
1. Explain the procedure to obtain supersonic nozzle contour for a given Mach number using method of characteristics. 5
An incident shock wave angle of 35 degrees impinges on a straight wall. If the upstream flow properties are M P 1 atm and T =300 calculate the reflected shock wave angle with respect to the wall and the flow properties P and T downstream of the reflected shock wave. 5
2. Differentiate between nozzle and venturi. State the necessary conditions for a choked flow to occur in a nozzle. 5
A diffuser has exit throat area ratio of 1.5 to 1. The inlet Mach number is 0·8. The initial pressure and temperature are 1 bar and 15°C. Assuming the flow to be isentropic, calculate the following for air: 5
Exit pressure
Exit temperature
Exit Mach number
3. Derive the energy equation for one-dimensional steady compressible flow from first principle. Deduce the isentropic relation between stagnation and sonic conditions for temperature, pressure and density. 6
Sketch the shock polar for M 2·5 and explain the method of finding the Mach numbers and shock angles for a turning angle of 5 degrees. 4
4. Answer any four of the following questions in brief: 4 x 2 1/2 =10
What is displacement thickness?
State the limitations of lifting line theory.
Explain the assumption of horse-shoe vortex.
What is boundary layer?
Define centre of pressure.
What is shock polar?
5. Derive the relation between Mach number and flow properties, viz., pressure, temperature and density across a normal shock wave. 5
State and explain the expression for linearized supersonic pressure coefficient. What are the assumptions made Enumerate. 5
6. Derive the relationship between the ratio of stagnation pressure to static pressure and Mach number for an isentropic flow. Derive the similar relations for temperature and density ratios. 6
A wedge of variable half angle is kept in a supersonic stream of Mach 2. Determine the maximum half angle up to which attached shock is possible. 4
7. What is the principle of operation of a typical shock tunnel? For an oblique shock wave, derive the relationships between the flow parameters in front of the shock and behind the shock. 10
8. Differentiate between static and stagnation temperatures. 5
Calculate the velocity of sound and the stagnation temperature of a jet at 300 K. Assume Mach number of 1.2. 5
9. Derive an expression for velocity of sound in air and show that it is proportional to the square root of absolute temperature of air. 10
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Subjects
- Aerodynamics- I
- Aerodynamics- II
- Aircraft Design/Launch Vehicle/ Rocket Design
- Aircraft Instruments
- Aircraft Safety and Maintenance Engineering
- Aircraft Structures
- Aircraft Systems And Airworthiness Requirements
- Applied Chemistry
- Applied Physics
- Basic Control Theory
- CNS-ATM system
- Composite Materials
- Computer Fundamentals
- Engineering Drawing
- Environmental Science
- Flight Mechanics
- High Speed Aerodynamics
- Instruction To Computer Play Device
- Introduction to Aeronautics
- Introduction To Rocket And Missiles
- Mechanics Design
- Propulsion- I
- Propulsion- II
- Rocket Propulsion
- Space Dynamics
- Strength of Materials
- Technical Writing and Communication Skills
- Workshop Technology