Out of interest I ran the figures for the CF6 through NASAs educational software and it came up with the following
Code:
ALTITUDE SPEED CORE FUEL FLOW GROSS RAM NET
(MPH) FLOW (LB/S) (PPH) THRUST DRAG THRUST
0 0 254 13820 45,171 0 45,171
0 170 262 14062 47,415 8,716 38,699
3,000 282 251 13511 47,256 14,146 33,109
35,000 .85M 103 6501 23,183 11,382 11,801
It should be noted that the air meeting the compressor face is not at free stream velocity (speed of the aircraft). The inlet is designed to slow the airflow so that it is presented to the compressor at a speed of .5M or less, to avoid choking the compressor. The ram drag above, is the drag associated with slowing down the free stream air as the air is brought inside the inlet. Even the SR-71 at 3.2M has the air delivered to the compressor at approx .5M.
Of interest also is the J-58 installed in the SR-71. At 3.2M, 54% of the thrust is provided by the differential pressure between the internal and external surfaces of the inlet spike. Of the remainder, 17% is provided by the engine and 29% by the ejector (the afterburner, which is in ram jet mode at this speed - air being tapped off the 4th stage compressor, diverted around the turbine, and injected into the afterburner)
I've tried reformatting with little luck - hope you can make sense of it.