Nozzle Area-Mach Visualizer

Visualize Mach distribution and exit isentropic state for a converging-diverging nozzle area ratio.

visual calculatorCompressible Flow

Read the flow shape before trusting the number.

This page turns a CFD setup into regime, scale, and dominant-effect cues. Adjust the calculator below and compare the moving graphic with the computed result.

input scale

model

check

compressiblenozzlearea-Machvisualization

formula

KaTeX rendered

\begin{aligned}\text{A/A* = (1/M) [2/(gamma+1) (1 + (gamma-1) M\^{}2 / 2)]\^{}((gamma+1)/(2(gamma-1)))}\end{aligned}

ASCII source

A/A* = (1/M) [2/(gamma+1) (1 + (gamma-1) M^2 / 2)]^((gamma+1)/(2(gamma-1)))

gammaA_exit / A_throatexit branch

exit Mach

2.3986

p_exit / p0

0.0685

T_exit / T0

0.4650

static pressure drop

0.9315

Use the supersonic branch for a choked converging-diverging nozzle without an internal shock. Switch branch to see the alternate area-Mach solution.

compressible nozzle area-Mach visualization