T.Z
20th Mar 2012, 11:01
I am trying to figure out how the thrust produced by a turbofan engine changes with altitude and speed - specifically I would like to know this for the RR Trent 556 (that are on the A340-600).
I know that thrust changes with altitude and velocity. The change with velocity also seems to be less with increase in altitude. The most common is to assume that the thrust is proportional to the change in air density:
T=T_0*(rho/rho_0)
though this is not too accurate.
I was wondering if anyone could help me get a more accurate model for this variation of thrust or help me obtain data specific for the RR Trent 556 engine.
I really appreciate any all help!
Thanks:ok:
I know that thrust changes with altitude and velocity. The change with velocity also seems to be less with increase in altitude. The most common is to assume that the thrust is proportional to the change in air density:
T=T_0*(rho/rho_0)
though this is not too accurate.
I was wondering if anyone could help me get a more accurate model for this variation of thrust or help me obtain data specific for the RR Trent 556 engine.
I really appreciate any all help!
Thanks:ok: