Re: Fluid Variable Intakes (Re: fun with expendable SSTOs ...)
- From: "Jeff Findley" <jeff.findley@xxxxxxxxxxxxxx>
- Date: Tue, 20 Mar 2007 08:45:51 -0400
"Craig Fink" <WeBeGood@xxxxxxxxx> wrote in message
news:AfQLh.129444$_73.8880@xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxx
Fluid Variable Intakes
For Acceleration type mission profiles with Turbojet, Ramjet, and
Scramjet.
Fluid Variable Intakes fix many of the difficult problems associated with
these engines, making it possible to use a single fixed inlets or a much
less complex inlet. As the aircraft passes the maximum design Mach Number
for the inlet, a fluid is used to compensate for the changing area ratio
between the beginning of the inlet and the sonic throat. Cryogenic Oxygen
/
Gaseous Oxygen being the fluid, also enriches the air taken in by the
engine with Oxygen, enhancing the performance when it is needed to
continue
to accelerating.
This isn't the sort of thing you can do with out *a lot* of detailed
aerodynamic, combustion, and thermal analysis. Not to mention how much wind
tunnel time this sort of research would consume. This is the sort of thing
that can easily burn a billion dollars worth of research grants and never
fly real hardware. Remember NASP? And NASP was easier than an accelerator
since it would have been optimized for supersonic cruise.
So, where's the papers? Certainly someone who's done the work has produced
a few dozen AIAA papers, right? I'm sure we'd all be interested in the
detailed analysis. Until then, liquid fueled rocket engines are the
preferred off the shelf solution to getting to orbit.
Jeff
--
"They that can give up essential liberty to obtain a
little temporary safety deserve neither liberty nor
safety"
- B. Franklin, Bartlett's Familiar Quotations (1919)
.
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