Develop the energy equation for the fluid flow in the integral form.
Based upon this derive the energy equation for the steady, inviscid, adiabatic fluid flow devoid of anybody forces, in the differential form.
Develop the stream functions for uniform flow, source flow and sink flow.
Illustrate the different coefficients of drag over the airfoil and an aircraft.
Illustrate in brief D’Alembert’s paradox.
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.
Illustrate the expressions for boundary layer thickness over the flat plate in laminar and turbulent boundary layers, describing all the parameters clearly.
Illustrate out the thermal boundary layer.