of the exhaust the pressure at the nozzle exit (p e ) the thrust of the system is explained using “thrust equation” f=m dot*v e +(p e -p 0 )*a e where, f is the thrust m dot is the mass flow rate v e is the exit velocity p e is the exit pressure p 0 is the free...
Since the nozzle area is πr2πr2, the thrust equation you provide seems logical, while mine less so... I therefore carefully went over the derivation, but realized that I don't have a mistake. Here is why equation you cite is wrong. First, just the pressure difference between the ...