Thrust application point location

[Don Stauffer <stauffer@xxxxxxxxxxxx>]

> Where is the Thrust application point located on a turbojet? on a
> rocket?
> 

It is transferred through all the nozzle, combustion chamber other 
internal structure to the mounting points.

In non-swiveling nozzles most engines are  pretty much axi-symmetric so 
the thrust vector is forward, so there is little concern about torques 
on mounts.  This is NOT so with swiveling nozzles, and one would have to 
look in detail at a particular engine.  I suspect the design predictions 
are not perfect and must be verified by load cells at attach points 
during testing, with measurements at each deflection angle.

As far as theory is involved, a rocket is easier to understand than a 
turbojet.  If you integrate the pressure over the entire surface of the 
chamber and nozzle, this will give you a thrust vector.