PTU B.Tech Aerospace Engineering 5th Semester May 2019 60521 AERODYNAMICS II Question Papers

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Roll No. | [ | [ 1] [ | Total No. of Pages : 02

Total No. of Questions : 09

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B.Tech.(ANE) (Sem.=5)

AERODYNAMICS - II

Subject Code : ANE-312

M.Code : 60521

Time : 3 Hrs. Max. Marks : 60

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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.

SECTION-A

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1. Explain the followings briefly:
   1. Potential flow
   2. Whitcomb's Area rule
   3. Supercritical airfoil
   4. Downwash
   5. Swept wing

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   6. Helmholtz's theorem
   7. Drag Polar
   8. Supercritical aerofoil
   9. Flapped aerofoil flowfield
   10. Ground effect

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SECTION-B

1. Explain briefly the significance of lift curve (Cl - a). What are the factors by which the maximum lift coefficient gets effected for a finite wing, explain.
2. Theoretical lift coefficient for a thin, symmetric airfoil in an incompressible flow is C_l = 2p a. Calculate the lift coefficient for M₈ = 0.7. Suggest improved compressibility correction method.

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3. Derive the fundamental equation of Prandtl's lifting line theory.
4. State the assumptions for thin aerofoil theory and explain important results of thin aerofoil theory for a symmetrical aerofoil.
5. Derive an expression for velocity potential equation. State the necessary assumptions.

SECTION-C

1. Draw a neat sketch of leeward vortex flow field over a delta wing and explain the spanwise pressure distribution.

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2. Describe source panel method for simulating the non-lifting flow over a circular cylinder.
3. Write short notes on the following :
   1. Blasius Theorem
   2. Kutta Joukowski Transformation

NOTE : Disclosure of Identity by writing Mobile No. or Making of passing request on any page of Answer Sheet will lead to UMC against the Student.

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