Out of interest with any successor to concorde, what lift/drag ratio is now technically possible, and likewise from more advanced powerplants that could be available now what lb/hr/lbf numbers could be achieved?
One other question if I may - how much of a compromise was concorde's wing with respect to the balance of supersonic vs sub-sonic efficiency? What I'm trying to ask is if the wing could be a variable geometry with no weight cost (impossible I know) how much more efficient could the supersonic wing have become - or was the compromise very much on the sub-sonic performance and not much to gain in terms of supersonic efficiency?
Once more - thanks for all the great answers to the really intriguing questions!! I'm fascinated by Concorde - and regret I never had the means to fly on her whilst she was still where she belongs!