PTU B.Tech Aerospace Engineering 3rd Semester May 2019 60502 AERODYNAMICS I Question Papers

Roll No.

Total No. of Pages : 02

Total No. of Questions : 09

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B.Tech.(ANE)/(Aerospace Engg.) (2012 Onwards) (Sem.-3)

AERODYNAMICS-I

Subject Code : ANE-203

M.Code: 60502

Time: 3 Hrs.

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Max. Marks : 60

INSTRUCTIONS TO CANDIDATES :

1. SECTION-A is COMPULSORY consisting of TEN questions carrying TWO marks each.
2. SECTION-B contains FIVE questions carrying FIVE marks each and students have to attempt any FOUR questions.
3. SECTION-C contains THREE questions carrying TEN marks each and students have to attempt any TWO questions.

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SECTION-A

1. Answer briefly :
   1. Pathline
   2. Potential flow
   3. Conservation equations
   4. Centre of pressure

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   5. Aerodynamic force
   6. Lift coefficient
   7. Pressure coefficient
   8. Steady-incompressible flow
   9. Two dimensional flow separation

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   10. Boundary Layer

SECTION-B

2. Define circulation, angular velocity, vorticity and time rate of strain of a fluid element in three-dimensional space.
3. Starting from the first principle. Derive Euler Equation of motion.

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4. Describe Doublet flow. Derive the velocity potential and stream function for it.
5. Explain, why a laminar boundary layer separates more easily than a turbulent boundary layer.
6. Derive an expression for velocity potential and stream function for a vortex flow.

SECTION-C

7. Show that the pressure coefficient around a circular cylinder placed in an ideal, incompressible flow is given by : Cp = 1.-4 sin² 0. Where '0' is the angular coordinate on the surface of the cylinder measured from the lagging stagnation point.

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8. Derive an expression for 2-D continuity equation applicable to compressible, viscous, non-uniform and unsteady flows. What are the advantages of integral form of continuity equation over the differential form?
9. Write short notes on the followings :
   1. Kantian's Integral equation
   2. Blasius solution for a flat plate

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