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1 Geometry
1 Mesh
1 Simulation setup
0 ResultsThe goal of this project is to reproduce and assess the numerical results reported in “Numerical Modeling of Supersonic Flow Through a Ramjet Nozzle Using Ansys Fluent.” A two-dimensional, steady-state, compressible CFD simulation will be performed in ANSYS Fluent using a density-based solver, the energy equation, and the k–ω SST turbulence model. The nozzle geometry and operating conditions will follow the paper, including a chamber total pressure of 2.27 MPa and a total temperature of 1200 K. The chamber-to-ambient pressure ratio will be varied, with particular attention to the reported optimum of approximately 57. Mesh independence and solution convergence will be checked. The predicted pressure, temperature, Mach number, discharge coefficient, and thrust coefficient will be compared with the published results to quantify agreement and identify possible causes of discrepancies.
by slilbaekslilbaek
khanhisthebest created this project
7 days ago
1 Geometry 1 Mesh 1 Simulation setup 0 ResultsThe goal of this project is to reproduce and assess the numerical results reported in “Numerical Modeling of Supersonic Flow Through a Ramjet Nozzle Using Ansys Fluent.” A two-dimensional, steady-state, compressible CFD simulation will be performed in ANSYS Fluent using a density-based solver, the energy equation, and the k–ω SST turbulence model. The nozzle geometry and operating conditions will follow the paper, including a chamber total pressure of 2.27 MPa and a total temperature of 1200 K. The chamber-to-ambient pressure ratio will be varied, with particular attention to the reported optimum of approximately 57. Mesh independence and solution convergence will be checked. The predicted pressure, temperature, Mach number, discharge coefficient, and thrust coefficient will be compared with the published results to quantify agreement and identify possible causes of discrepancies.
