Flows in Converging-Diverging Nozzles

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This simulation concerns profiles of pressure, temperature and Mach number in Laval Nozzles. Use the slider to change the back pressure, and then press recalculate. The underlying theory is summarised in Sections 4 and 5 of the linked note . Click here for versions of the isentropic flow tables and normal shock tables .

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Choose type of plot: Pressure Temperature Mach number Area

Fixed Parameters:     Gamma:      A_exit/A_throat:  

Back pressure (0-100%max):     Critical pressure     Design pressure

Recalculate       Describe flow

List of key values.

Critical pressure: \( p_{crit}/p_{o1}= \) -- .

Design pressure: \( p_{des}/p_{o1}= \) -- .

Pressure at throat: \( p_{throat}/p_{o1}= \) -- .

Pressure at exit: \( p_{exit}/p_{o1}= \) -- .

Stagnation pressure at exit: \( p_{o2}/p_{o1}= \) -- .

Choked area: \( A^*/A_{throat}= \) -- .

Design Mach no at exit: \( M_{des}= \) -- .

Mach no at throat: \( M_{throat}= \) -- .

Mach no at exit: \( M_{exit}= \) -- .