Why Are L/D Ratios Lower at Supersonic Speed?
I'm curious to an actual reason why L/D ratios tend to be lower at supersonic speed compared to subsonic speed.
I've generally assumed it had to do with the fact that you'd have more drag due to the effects of shockwaves, more turbulence; less lift due to a lower pressure-differential among the upper and lower section of the wing, and the fact that the center of pressure moves aft requiring more nose-up trim to keep the plane level.