Recently I took a look at this paper:
“Electrically Driven Supersonic Combustion”, Energies 2018, 11, 1733; doi:10.3390/en11071733 https://www.mdpi.com/1996-1073/11/7/1733
It made me think about how this might be used as a stage for a rocket that could bring it to a very high velocity, and a sub orbital trajectory. From what I understand this could allow for a much smaller first stage as well as a second stage that could build up a good deal of velocity at a lower altitude without the need for oxidizer along with less propellant. (Please correct me on any misunderstandings or ignorance on that.)
If this Plasma Scramjet was capable of being used as a stage for a spacecraft what would it look like? For example, could a smaller booster be used to accelerate it up to its working velocity and altitude? after which the Plasma Scramjet would be able to add accelerate the craft to a higher speed at a shallower angle. If this was done; (Hypothetically, not necessarily if this is simpler or cheaper) how would the actual craft have to be designed differently from a conventional rocket?
On an extra note, if anyone wants to answer a related question. Does this engine have the potential to make sub-orbital high speed commercial flights financially viable? Could we expect to have access to high speed transcontinental flights in minutes rather than hours in the near future?