Exam Details
| Subject | low speed aerodynamics | |
| Paper | ||
| Exam / Course | b.tech | |
| Department | ||
| Organization | Institute Of Aeronautical Engineering | |
| Position | ||
| Exam Date | July, 2018 | |
| City, State | telangana, hyderabad |
Question Paper
Hall Ticket No Question Paper Code: AAE004
INSTITUTE OF AERONAUTICAL ENGINEERING
(Autonomous)
B.Tech IV Semester End Examinations (Supplementary) July, 2018
Regulation: IARE-R16
LOW SPEED AERODYNAMICS
Time: 3 Hours Max Marks: 70
Answer ONE Question from each Unit
All Questions Carry Equal Marks
All parts of the question must be answered in one place only
UNIT I
1. Define velocity potential and derive the relationship between the stream function and velocity
potential.
Define stream function and write the expressions in Cartesian and Polar coordinates.
2. Derive the expressions for streamlines in doublet flow with neat sketch.
Explain Kutta-Joukowski theorem with an appropriate sketch. Write down the assumptions.
UNIT II
3. Sketch the airfoil and explain its nomenclature. Differentiate between symmetric and cambered
airfoil.
Derive the expression to calculate the aerodynamic center. What is the physical significance of
it?
4. Explain the thin airfoil theory with neat sketch. Write down the assumptions taken to derive it.
Explain the high lift devices with appropriate diagram.
UNIT III
5. Briefly explain the vortex system with relevant diagrams.
Explain the following
i. Helmholtz's theorem
ii. The Biot-Savart law
6. Explain Prandtl's classical lifting theory and write the fundamental equation for circulation
distribution.
Explain the source panel and vortex panel methods and write the governing equations.
Page 1 of 2
UNIT IV
7. Explain the effect of wing body interference with neat sketch.
Define D-Alembert Paradox. Is there any lift produced without viscous effect?
8. Explain the method of singularities using Prandtl-Glauret singularity method.
Discuss the effects of propeller on the aircraft wing and airplane dynamics.
UNIT V
9. Sketch the boundary layer on a flat plate and mention the velocity profile and temperature profile.
Sketch and explain the laminar and turbulent boundary layer. Which one has more skin friction
drag?
10. Derive the expressions for
i. Kinetic energy thickness
ii. Momentum thickness
Write the expression for displacement thickness. What is the purpose of finding displacement
thickness?
INSTITUTE OF AERONAUTICAL ENGINEERING
(Autonomous)
B.Tech IV Semester End Examinations (Supplementary) July, 2018
Regulation: IARE-R16
LOW SPEED AERODYNAMICS
Time: 3 Hours Max Marks: 70
Answer ONE Question from each Unit
All Questions Carry Equal Marks
All parts of the question must be answered in one place only
UNIT I
1. Define velocity potential and derive the relationship between the stream function and velocity
potential.
Define stream function and write the expressions in Cartesian and Polar coordinates.
2. Derive the expressions for streamlines in doublet flow with neat sketch.
Explain Kutta-Joukowski theorem with an appropriate sketch. Write down the assumptions.
UNIT II
3. Sketch the airfoil and explain its nomenclature. Differentiate between symmetric and cambered
airfoil.
Derive the expression to calculate the aerodynamic center. What is the physical significance of
it?
4. Explain the thin airfoil theory with neat sketch. Write down the assumptions taken to derive it.
Explain the high lift devices with appropriate diagram.
UNIT III
5. Briefly explain the vortex system with relevant diagrams.
Explain the following
i. Helmholtz's theorem
ii. The Biot-Savart law
6. Explain Prandtl's classical lifting theory and write the fundamental equation for circulation
distribution.
Explain the source panel and vortex panel methods and write the governing equations.
Page 1 of 2
UNIT IV
7. Explain the effect of wing body interference with neat sketch.
Define D-Alembert Paradox. Is there any lift produced without viscous effect?
8. Explain the method of singularities using Prandtl-Glauret singularity method.
Discuss the effects of propeller on the aircraft wing and airplane dynamics.
UNIT V
9. Sketch the boundary layer on a flat plate and mention the velocity profile and temperature profile.
Sketch and explain the laminar and turbulent boundary layer. Which one has more skin friction
drag?
10. Derive the expressions for
i. Kinetic energy thickness
ii. Momentum thickness
Write the expression for displacement thickness. What is the purpose of finding displacement
thickness?
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