Exam Details
| Subject | Aerodynamics- I | |
| 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-0121
B.Tech. AEROSPACE ENGINEERING
(BTAE)
Term-End Examination
December, 2016
OU04...:S BAS-012 AERODYNAMICS
Time hours Maximum Marks: 70
Note: Attempt any Beven questions. All questions carry equal marks. Use of scientific calculator is permitted.
1. Define the following:
Centre of Pressure
Aerodynamic Centre
Jet Flap
Stall Condition
What is the difference between Euler's model and Navier-Stokes model of equations Write' the· generic form of Navier-Stokes equations. 5+5
2. Briefly explain the flow in a C-D nozzle with the help of a neat sketch.
What are the characteristics of a vortex flow State and prove the Kutta-Zhukovsky theorem. 5+5
3. Draw a neat sketch of a supersonic wind tunnel circuit and explain the function of each component.
Discuss lift on rotating cylinder in uniform flow. 5+5
4. How does Van der Waals equation differ from ideal gas equation? Explain.
A point source is a point where an incompressible fluid is imagined to be created and sent out evenly in all directions. Determine its velocity potential and stream function. 5+5
5. If the stream function for steady flow is given by w y2 — x2, determine whether the flow is rotational or irrotational. Then determine the velocity potential
The stream function for a two-dimensional flow is given by 2xy. Calculate the velocity at the point 3). Also find the velocity potential function. 5+5
6. Distinguish between the following:
Steady and Unsteady flow
Rotational and Irrotational flow
In a two-dimensional incompressible flow, the fluid velocity components are given by
u =x-4yand v
Show that the velocity potential exists and determine its form. Also find the stream function. 5+5
7. Differentiate between the following:
Streamlined body and Bluff body
Friction drag and Pressure drag
A flat plate 2 m x 2 m moves at 40 km/hour in stationary air of density 1.25kg/m3. If the coefficient of drag and lift are 0.2 and 0.8 respectively, find
the lift force,
the drag force,
the resultant force, and
the power required to keep the plate in motion. .5+5
8. Define Doublet. Draw its streamlines.
How are streamlines and equipotential lines related to each other? Explain. 5+5
9. Write short notes on any two of the following: 2*5=10
Magnus Effect
Boundary Layer
Pitching Moment
Mach Number
B.Tech. AEROSPACE ENGINEERING
(BTAE)
Term-End Examination
December, 2016
OU04...:S BAS-012 AERODYNAMICS
Time hours Maximum Marks: 70
Note: Attempt any Beven questions. All questions carry equal marks. Use of scientific calculator is permitted.
1. Define the following:
Centre of Pressure
Aerodynamic Centre
Jet Flap
Stall Condition
What is the difference between Euler's model and Navier-Stokes model of equations Write' the· generic form of Navier-Stokes equations. 5+5
2. Briefly explain the flow in a C-D nozzle with the help of a neat sketch.
What are the characteristics of a vortex flow State and prove the Kutta-Zhukovsky theorem. 5+5
3. Draw a neat sketch of a supersonic wind tunnel circuit and explain the function of each component.
Discuss lift on rotating cylinder in uniform flow. 5+5
4. How does Van der Waals equation differ from ideal gas equation? Explain.
A point source is a point where an incompressible fluid is imagined to be created and sent out evenly in all directions. Determine its velocity potential and stream function. 5+5
5. If the stream function for steady flow is given by w y2 — x2, determine whether the flow is rotational or irrotational. Then determine the velocity potential
The stream function for a two-dimensional flow is given by 2xy. Calculate the velocity at the point 3). Also find the velocity potential function. 5+5
6. Distinguish between the following:
Steady and Unsteady flow
Rotational and Irrotational flow
In a two-dimensional incompressible flow, the fluid velocity components are given by
u =x-4yand v
Show that the velocity potential exists and determine its form. Also find the stream function. 5+5
7. Differentiate between the following:
Streamlined body and Bluff body
Friction drag and Pressure drag
A flat plate 2 m x 2 m moves at 40 km/hour in stationary air of density 1.25kg/m3. If the coefficient of drag and lift are 0.2 and 0.8 respectively, find
the lift force,
the drag force,
the resultant force, and
the power required to keep the plate in motion. .5+5
8. Define Doublet. Draw its streamlines.
How are streamlines and equipotential lines related to each other? Explain. 5+5
9. Write short notes on any two of the following: 2*5=10
Magnus Effect
Boundary Layer
Pitching Moment
Mach Number
Other Question Papers
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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