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problem 1:

Develop the energy equation for the fluid flow in the integral form.

problem 2:

Based upon this derive the energy equation for the steady, inviscid, adiabatic fluid flow devoid of anybody forces, in the differential form.

problem 3:

Develop the stream functions for uniform flow, source flow and sink flow.

problem 4:

Illustrate the different coefficients of drag over the airfoil and an aircraft.

problem 5:

Illustrate in brief D’Alembert’s paradox.

problem 6:

Illustrate, with the aid of appropriate sketches, flows over the airfoil ata low (say, 5 degree) angle of attack and the high (say, 20 degree angle of attack) over a symmetric airfoil.

problem 7:

Illustrate the expressions for boundary layer thickness over the flat plate in laminar and turbulent boundary layers, describing all the parameters clearly.

problem 8:

Illustrate out the thermal boundary layer.

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