Blackbird's thrust question
Please can someone give some ideas?
The following extract comes from "F-12 series aircraft propulsion system performance and development" by D. Campbell
BTW Was unable to include Table 1 but it just shows usual falling contribution from the engine mounts with speed.
"In order to understand the importance of each of
the three propulsion system components, it is interesting
to note the proportion of the thrust which is supplied by
each component while operating in maximum afterburner.
Table 1 indicates how the actual thrust forces are distributed
while the engine is inducing flow and heating it
up with maximum afterburner. If the AB is reduced to
minimum AB, the engine would actually be dragging on
the engine mounts at high Mach numbers. Further reduction
of engine thrust below military power will result in no
propulsive thrust on the aircraft."
Q referring specifically to 'is inducing flow and heating it up with maximum afterburner'
I take this to refer to the induced secondary flow which flows over the red-hot afterburner casing and the intimation that this is significant in producing thrust. However due to the high air flow rate (1/3 intake entry flow) and it being a poor design of heat exchanger would the heat transfer really be significant (ie per lb/sec)?
Do I have the wrong end of the stick?
Thank you.