For the free stream Mach numbers ranging from 0.1 to 0.8, graph the increase in Mach number, ΔM, as a function of pressure coefficient. Use a range of C p between −2 and 0. Wave Drag 6.8 Show that...

For the free stream Mach numbers ranging from 0.1 to 0.8, graph the increase in Mach number, ΔM, as a function of pressure coefficient. Use a range of C_p
between −2 and 0.

Wave Drag

6.8 Show that (6.22) can be derived from (6.19), (6.21), and (2.106).

6.9 Consider the perturbed momentum equation in integral form (6.26).

(a) Show that, by employing the continuity equation (6.27), this equation can be simplified according to:

(b) Argue that the expression above is identical to (6.28) because we integrate over an enclosed surface, S.