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CFD |Thermal| Machine Learning Engineer
Project Summary : National Aerospace Labotories:
Simulations of Mach 2.9 turbulent shear layer in a back-step/ramp configuration and Mach 4-5 flow in supersonic inlet-isolator.
1)Literature survey for academic benchmark cases and experimental/LES data sets.
2) Careful grid generation using meshing tool Gridgen/Pointwise and Automating repeated tasks using Pointwise Glyph scripting(TCL).
3) Running In-hose hybrid RANS-LES code on selected benchmarking cases and Post-processing the results using visualization tool TECPLOT 360EX/GNUplot.
Some Results:
3
Pointwise grid for supersonic backstep/ramp configuration.
2
Supersonic inlet mesh using Pointwise.
contour
Mach 2.9 turbulent shear layer in a back-step/ramp con guration.
contr-p
Numerical simulation of Mach 5 flow in supersonic inlet-isolator for ramjet.
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