Oleg Zabluda's blog
Thursday, August 09, 2018
 
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BFR [...] would be the most efficient launch vehicle to LEO ever, besting the latest record holder, the expendable version of the Falcon Heavy launch vehicle (4.49% of launch mass), by over half a percent. [...] thrust to weight ratio of 1.36 to 1, which meant the launch vehicle could potentially lift even more with larger propellant tanks.
[...]
capable of lifting more than 300 tonnes to LEO. [...] due to its sheer size and the high ISP of its engines, barge landing reuse would only cost about 4% of the rocket’s maximum capability.
[...]
SpaceX’s grand ambitions finally became fully apparent when the launch vehicle’s expendable payload capacity of 550 tonnes was announced. The rocket would be 133% more capable than the version SpaceX had planned just the year before.

This incredible performance was enabled by the Raptor engine. Its sea level thrust had increased by 55.5% from 1,961 kN (440,850 lbf) to 3,050 kN (685,667 lbf), its sea level ISP was up 3.9% (334 seconds versus 321.4 seconds prior), it was now capable of throttling 20-100%, and its 300 bar chamber pressure was the highest in rocket engine history.

Its vacuum version would feature an even higher thrust of 3,500 kN (786,831 lbf) and an ISP of 382 seconds, the highest hydrocarbon ISP engine on record, thanks to a very large 200 to one expansion ratio nozzle.
[...]
could deliver up to 450 tonnes of cargo to Mars.
[...]
Each stage would boast a modest delta wing and four landing legs, allowing the stage to de-orbit and land vertically.
"""
https://www.nasaspaceflight.com/2018/08/evolution-big-falcon-rocket
https://www.nasaspaceflight.com/2018/08/evolution-big-falcon-rocket

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