First I would like to agree with others on the priceless content of this Concorde forum. The published books are gems in their own right but always leave more questions than could ever be answered without all your input.
Whilst looking for some engineering background on the intake flow I came across this paper which goes into some detail
https://docs.google.com/viewer?a=v&q...70XxfUcy8PWNyw
The author says for example "..pressure recovery at Mach2 was 95%, with 1% of the loss attributed to subsonic diffusion,0.5% to the 1st shock,, 0.02% to the 2nd and 3.7% to the 3rd and final oblique shock."
I was looking for mention of a normal shock as I always understood that was a prerequisite for finally getting to subsonic.
A normal shock is only mentioned in connection with an alternative design with a lengthened forward ramp.
So, was there one or not? Or is it just not that simple?
Thanks.