Air enters subsonically from standard atmosphere and flows isentropically through the frictionless and adiabatic converging-diverging duct having a circular cross-sectional area, A, that varies with axial distance from the throat, x, according to the formula
A = 0.1 + x2
where A is in square meters and x is in meters. The duct extends from x = - 0.5 m to x = + 0.5 m. Determine
(a) the ratio of duct exit pressure to duct inlet stagnation pressure that will result in a standing normal shock at x = + 0.3 m;
(b) the stagnation pressure loss.