Numerical Modeling of Supersonic Flow Through a Ramjet Nozzle Using Ansys Fluent

A ramjet nozzle was designed for supersonic operating conditions and evaluated numerically using Ansys

Fluent 16.1 over a range of chamber-to-ambient pressure ratios. The nozzle geometry was generated to achieve

smooth, shock-free expansion under supersonic outflow conditions using the characteristic curve method at a specific

nozzle chamber pressure and temperature using Matrix Laboratory (MATLAB) and then validated by comparing

the numerical predictions with available experimental data. The results show that a pressure ratio of 57 provides the

highest thrust coefficient (TC), while lower ratios lead to over-expanded flow and higher ratios to under-expansion

with increased shock losses. Contours of pressure, temperature, and Mach number confirm the expected supersonic

flow structure and demonstrate that the nozzle achieves optimum performance under the identified conditions.

ATHEER RAHEEM ABDULLAH

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