A nozzle at pb/p₀ = 0.70: shock in the divergent section
The duct above, and the static pressure along it below, computed station by station from the local area. Where a shock stands inside the divergent section its position was solved for rather than placed: the shock spends total pressure, which sets the subsonic Mach number at the exit, which has to match the imposed back pressure.
10 essays call
nozzle-duct. The drawing above is what it returns with no arguments at all; every
call below passes it something, because a placement that passes nothing draws whichever member
of the family the generator happens to default to rather than the one its essay argues about.
It is also the blast radius. Changing nozzle-duct changes every figure listed here
at once, and on this site it may change what they assert as well as what they show —
which is what has to be rebuilt and looked at before the change is believed.
Where it is called
What each of these essays asks for instead of the defaults is on the regime index, which reads the parameters back out of the finished figures rather than out of the placements.
- The duct that works backwards Compressible flow
- The throat that stops listening Compressible flow
- One area, two answers Compressible flow
- The depth that costs least Fluids at work
- The jump the equations allow Compressible flow
- The only law that forbids it Compressible flow
- What a shock costs Compressible flow
- Two ways to choke Compressible flow
- The jet a cone sprays sideways Compressible flow
- Friction moves the sonic point past the throat Compressible flow