Hello there, My name is joe.
Currently i am a student embarking on a project for jet propulsion test rig.
I really need to clarify certain doubts that had been bugging me.
If i am not wrong Thrust equation at take off follows as Ae(Pe-Pa) + M(Ve) ........ (1)
Where Ae = Area at exit, Pe = Pressure at exit, Pa = Ambient pressure, M= Mass flow rate and Ve = air velocity at exit.
I got muddled in the following, when throat is chocked or critical condition, Mach no = 1. So when Mach no = 1, Ve= square root(YRTe) .............(2)
where Y and R are gas constants
It follows that Mass flow rate = density*Ae*Ve ....... (3)
It also follows that density = Pressure/(R*Te) .........(4)
subt (3) into (4) we have (Pe)(Ve)(Ae)/(R)(Te) = Mass flow rate
Now when i try to subt into my momentum thrust which is M(Ve) my temperature equation seems to be cancelled away.
from my theoretical calculation, it seems that temperature is not having significance in thrust which is totally wrong. Please could some one pin point my mistakes.
Thanks and i hope i am not being too draggy.