Wouldn't that show up as variation of c* efficiency? The models assume the
chemicals are fully involved, if a significant amount of propellants are
going out the nozzle unreacted then there would be a performance shortfall
between the real motor and the model.
Does non-lithiated HTPB run at 85% c* typical?
Do lithiated rocket programs take into account that lithiated propulsion
engineers will be less worried about performance numbers?
On Tue, May 3, 2022 at 6:28 PM Barry Jolly <1bcjolly@xxxxxxxxxxxxx> wrote:
Question: Do computer programs such as Micropep and NASA’s CET85 have the
ability to predict improvements in parameters, such as Isp, due to changes
in combustion phenomena? From my understanding of Alitec’s explanation,
their propellants increased performance is due to a difference in boiling
temperature of lithium as compared to aluminum in alloy form causing an
explosion of the alloy into nano-type particles which burn very close to
the surface of the propellant. Such explanation appears to me to be based
on burning characteristics of the propellant rather than differences
between enthalpies of propellant reactants and exhaust products.
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