Drag at supersonic speeds

Wed Mar 17, 1999 11:30 pm

I know that the Concorde uses afterburners until reaches a Mach 1.7 speed, after that shuts down them and smoothly accelerates up to Mach 2.0 (cruising speed) and 50.000 feet (cruising altitude).

Does it mean that once the sound barrier is broken and well surpassed (mach > 1.7) drag is lower than at subsonic speeds (Mach 0.8-0.99) if the altitude is near 50.000 feet?

If so, that would mean that once in Mach 2.0 the fuel compsumtion of a SST could be equal or lower than that of a subsonic airliner, which could mean that a supersonic transport could be economically affordable...

Any comments?



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