<p> [REGULATIONS-2008] AE1251 B.E./B.Tech DEGREE EXAMINATION, MARCH 2011 (Aeronautical Engineering) AERODYNAMICS-I TIME: 3 hours Maximum Marks: 100</p><p>PART –A (10x2=20 marks)</p><p>Answer ALL questions </p><p>1. State the law of conservation of mass.</p><p>2. What do you mean by steady flow and unsteady flow?</p><p>3. Write down the relation between vorticity and circulation.</p><p>4. Write down the continuity equation in Cartesian co-ordinate.</p><p>5. What is Kutta condition?</p><p>6. What is meant by circulation?</p><p>7. What is starting vortex?</p><p>8. State Kelvin’s circulation theorem.</p><p>9. Define shape factor.</p><p>10. Define energy thickness. PART –B (5x16=80 marks)</p><p>Answers ALL choosing either (a) or (b) of each questions</p><p>All questions carry equal marks</p><p>11. Derive the continuity equation for a generalized fluid flow in polar co-ordinates.</p><p>(16)</p><p>OR</p><p>12. Derive the energy equation for an incompressible fluid from the basic principle. (16)</p><p>13 (i) Define coefficient of pressure and plot the variation of coefficient of pressure for the circular cylinder kept in a uniform flow for both real and inviscid flows. (8)</p><p>(ii) Sketch the flow pattern around a spinning cylinder in a uniform stream for various circulation strength indicating clearly the movement of stagnation points. (8) OR</p><p>14. Explain the concept of source flow and derive velocity potential function from vortex strength ( (16)</p><p>15. Explain Kutta-Joukowski theorem and prove that L= (16)</p><p>OR</p><p>16. A long circular cylinder of radius K is placed in a steady horizontal stream of velocity U. The cylinder with an angular velocity Calculate the relation = (16)</p><p>17. The camber line of a circular arc aerofoil is given by-</p><p>Show that at zero lift angle, = -2h</p><p>OR 18. Derive the Prandtl's Lifting Line theory and write the assumptions made. (16) 19. If the velocity profile in boundary layer is assumed to be </p><p>= ( ) ─ ( )3; Calculate the thickness of the boundary layer, displacement thickness and momentum thickness the shear stress 1.5 m from the leading edge of a plate. (16)</p><p>OR</p><p>20. Write down the Navier Stokes equation for a laminar, unsteady, compressible, three dimensional viscous flow. (16)</p>