The crescent wing design seen on the Victor bomber seems to have a great number of advantages...
- the critical mach remains more constant along the span, so the formation of shock waves is more even and has less pitch trim changes at high speed
- higher inboard sweep at the point where the wing is the thickest increases the overall critical mach and thereby improves transonic performance
- the curvature (somewhat?) reduces spanwise flow, thereby lowering tip-stall effects at low speed
- when such a stall does occur, it happens at a point closer to the MAC, so the magnitude of the pitch-up is lower
- because of the geometry of the approach, some designs will have a natural flare built-in - this was a major positive benefit on the Victor, although not a design goal
So... with all of these advantages, why doesn't everyone use them? Is there some disadvantage that is not being mentioned?