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As an example the RL-10B2 hydrogen-fueled upper stage engine only has a chamber pressure about 40 bar but because it uses a long nozzle optimized for vacuum use, it gets a vacuum Isp of about 465 s, quite high.
In reality- not quite. The DIRECT study used 459 seconds for the RL-10B-2, and apparently it did not quite reach the ISP goal that was set for it. I may be wrong though, they could have just used the lower value to be conservative.
Then the suborbital companies engines could have orbital Isp's with longer nozzles.
1. Where is the MATH. I can say that I can turn Santa's sleigh into an SSTO too, a claim alone is unfortunately pretty useless.
2. Even with high expansion nozzles propellants have their limitations. Virgin Galactic's hybrid rocket won't have enough performance, XCOR, Blue Origin and Armadillo may have better luck however.
3. You can't just fit a nozzle extension to an engine. This is engineering, and as such there are limitations, practicalities and unknowns.
4. ISP isn't the only consideration in building an orbital vehicle. The suborbital tourism vehicles likely have too low a mass ratio to make orbit, even with higher performance engines.
However, another solution is to use altitude compensation methods.
Why can't you have a two-stager with altitude compensation? It could be very beneficial for a first stage to have altitude compensation.
This solution would make it possible for the suborbital companies to even field low cost SSTO's.
:dry:
Have you ever done a trade study to see if SSTOs really are lower cost than TSTOs?