Consider a Kantrowitz-Donaldson diffuser designed for a flightMach number of 1.8. The entrance area equals 3.0 ft2and the ambientairtemperature and pressure are 500ï‚°R and 0.8atmosphere. The flowis isentropic everywhere except across the normal shockwave.Determine:(a) the minimum cross-sectional area of the throat suchthat a normal shock may be stabilized at the entrance, (b) themaximum mass flow, and(c) the maximum stagnation pressure possibleat the end of the diffuser (with subsonic flow only in thedivergent portion).In each of these optimizations, consider theflight Mach number fixed at the design value while the finalpressure (at the end of the diffuser) is allowed to adjust.
