Assuming the inlet captures the entire flow at all flight Mach numbers, and the internal pressure is always high enough to stabilize a normal shock at the entrance of the internal duct, calculate and plot the stagnation pressure ratio across the combined shock system for the above flight Mach numbers.

x+2 because it just doubles hon so the pattern can actually tell you the expression.

so for example,

if x=2 then 2+2 is 4

if x=4 then 4+4 is 8

and so on and so forth.

i really hope that this makes sense and you out in a way hon: )

answer:

i lost in getting someone back.

i learned that people are really two-faced and no matter how angelic someone appears they always have a devil side and that you cant trust anyone anymore no matter how dear they are to you.

if your wondering who it waz it waz mah still miss her tho

~batmans wife dun dun