A subsonic diffuser flow is steady and adiabatic with inlet Mach number M1 = 0.6. Total pressure loss in the diffuser is 2% of the inlet total pressure, i. e., pt2/ pt1 = 0.98. The diffuser area ratio is A2/ A1 = 1.50. Assuming that the flow in the diffuser has a uniform exit flow, calculate the exit Mach number M2 the static pressure recovery in the diffuser CPR the (internal) force acting on the diffuser, i. e., Fx, wall, nondimensionalized by the inlet static pressure and ar

can you make it more obvious. i can't see it properly

answer:

d. attempt to find the owner, then leave your information if you cannot find them.

explanation:

d. represents both (b) and (c).

more logical as well.

b and c are to complicated.

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answer:

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answer:

yes that is right have a good day