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.