/sci/ - Science & Math

>>11731524
>Less per unit propellant mass consumed and per unit mass of engine hardware compared to an optimized bell nozzle.
Not when you compare an equivalent bell nozzle
>Only through additional weight and complexity,
Complexity sure, weight maybe not
>which in an idealized and perfect world aren't even an improvement over conventional nozzles,
Bold assumption considering the tech is in its infancy and was beating comparable bell nozzle engines.
>https://youtu.be/D4SaofKCYwo
If aerospikes had the same level of R&D that bell nozzles have enjoyed then we would probably be using aerospikes. Elon musk even said hes considered it in the above video