Fig. 1: Flow through a convergent-divergent (de Laval) nozzle.
From: Finding flows of a Navier–Stokes fluid through quantum computing
The nozzle profile is specified by its cross-sectional area A(x). Steady-state Mach number M(x), pressure P(x), mass density ρ(x), and temperature T(x) vary with nozzle position x as described in Supplementary Information SI-5B. a Absent a shockwave the flow enters at low Mach number M0 ≈ 0, is accelerated in the convergent section to sonic speed at the throat (M* = 1), then continues to accelerate to Me > 1 at the nozzle exit. b Here the flow contains a normal shockwave (red rectangle) in the divergent section of the nozzle. This can occur for a wide range of exit pressure values Pe. The flow enters at low Mach number M0 ≈ 0, is accelerated in the convergent section to sonic speed at the throat, then continues to accelerate until just before reaching the shockwave (M1 > 1). The flow then decelerates to subsonic speed (M2 < 1) in crossing the shockwave and continues to decelerate until reaching the nozzle exit.
