1 (a)
Define a fluid and distinguish between ideal and real fluids.

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1 (b)
A stone weights 2KN in air and 168N in water. Calculate the volume and specific gravity.

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1 (c)
Explain Hydrostatic law.

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1 (d)
Define steam lines, path lines and streak lines.

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1 (e)
Define Mach number, stagnation density and stagnation temperature.

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2 (a)
The velocity components in two dimensional flow fields are as follows

u=y

i) whether the flow is possible

ii) obtain an expression for steam function

iii) obtain an expression for potential function.

u=y

^{3}/3+2x-x^{2}y, v=xy^{2}-2y-x^{3}/3.i) whether the flow is possible

ii) obtain an expression for steam function

iii) obtain an expression for potential function.

10 M

2 (b)
A sliding gate 3m and 1.5m high situated in a vertical plane has a coefficient of friction between itself and guide of 0.18. If the gate weight is 19n and its upper edge is at a depth of 9m, what vertical force is required to raise it? Neglect buoyancy force on gate.

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3 (a)
Starting from the Navier Stokes equation for an incompressible Newtonian fluid derive Bernoulli's equation starting the assumptions.

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3 (b)
Derive the expression for stagnation density and stagnation temperature.

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4 (a)
A pipeline of length 2400m is used for power transmission. If 115KW power is to be transmitted through the pipe in which water having a pressure of 500 N/cm

^{2}at inlet is flowing? Find the diameter of the pipe and efficiency of transmission if the pressure drop over the length of pipe is 100 N/cm^{2}. Take f=0.026 also find diameter if pipe corresponding to maximum efficiency of transmission.
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Write short note on.

4 (b) (i)
Moody's diagram

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4 (b) (ii)
Major and minor losses.

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5 (a)
A normal shock wave occurs in a duct in which air is flowing at a Mach number of 1.5. The static pressure and temperature upstream of the shock wave is 1.5 bar and 270°C. Determine pressure, temperature and mach number downstream of the shock. Also calculate strength of shock.

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5 (b)
Explain Prandtl's mixing length theory.

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6 (a)
The velocity profile within a laminar boundary layer over a flat plate is given by the equation.

u/U =2(y/δ) - (y/δ)

Where U is the mean stream velocity and δ is the boundary layer thickness. Determine the displacement thickness and momentum thickness.

u/U =2(y/δ) - (y/δ)

^{2}Where U is the mean stream velocity and δ is the boundary layer thickness. Determine the displacement thickness and momentum thickness.

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Explain

6 (b) (i)
Aerofoil theory

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6 (b) (ii)
Reynolds Transportation theorem.

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