4 ms·
If I understood this table [1] correctly, theoretically these kind of engines could increase thermal efficiency by a lot , almost doubling them. Which of course
by montenegrohugo 6y ago
If I understood this table [1] correctly, theoretically these kind of engines could increase thermal efficiency by a lot , almost doubling them. Which of course would be incredible and result in a much higher payload/rocket percentage [2].
In terms of Isp, the same paper [1] quotes 1000-1200!!! Isp for small rotating detonation engines. Which is insane (state of the art rocket engines are around ~400)
[1] https://www.intechopen.com/online-first/a-theoretical-review-of-rotating-detonation-engines#tab1 https://www.intechopen.com/online-first/a-theoretical-review...
[2] https://en.wikipedia.org/wiki/Tsiolkovsky_rocket_equation https://en.wikipedia.org/wiki/Tsiolkovsky_rocket_equation
- baybal2 6y agoI think you are not reading it right. I think they are putting it for an air breathing version.
- montenegrohugo 6y agoYeah, that seems more plausible. Pity, it was the only source I found of ISP values of Rotating detonation engines. Now I still have no idea what kind of ISP increase we could see if RDE's were to be practical.
- valuearb 6y agoThe theoretical max for chemical rockets using standard fuels is around 530 using hydrogen. 1,000 requires it to be using the atmosphere, ie a jet.