There is a
nice Java applet showing shock angle as a function of mach
and the shape of the wedge going through the air. You can
also see
the formulas for shock angle and temperature.
There is also a
web page with more information on shock angles and it has
a fortran program to calculate it.
Another
web page has
another fortran program. And on the
aerospaceweb.org applet the "Oblique Shock Relations" will also
tell you shock angle.
These 2 different applets and 2 different programs all seem to get
about the same result. Also, these match
examples
In this simulator we currently assume that the specific heat of air
is constant at 1.4. Looking at
the properties of air the specific heat ratio does not seem to change much from 1.4. Not sure
how much error this introduces though.
In this simulator we use an ideal gas model. It turns out that
at high Reynolds numbers, the shock layer can be treated as inviscid
(meaning there is no friction). Also, the "caloric perfect gas
assumption" is not too bad, but at high
temperatures
some of the heat goes into chemical reactions in air and so
the caloric perfect gas assumption overpredicts the temperature.
So as I understand it, the the way the simulator works it is reporting
temperatures that are higher that in the real world. So if our SSTT design
can handle the temperatures indicated by the simulator then it can handle
the real world. Also, it
seems that we can keep under most of the chemically
reactive temperatures with the SSTT approach anyway.
A few other papers to look at:
The simulator massNoseAngle is the angle for an equivalent wedge.
They say that a
"relatively simple hypersonic flow analysis technique is an approximate
method based on equating the body of interest with a two-dimensional wedge
for modeling cones". So if the user really has some shape other
than a wedge they should apply this
relatively simple technique to generate an input angle for this simulator. :-).
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