Added figure: Mach-number contour through convergent-divergent nozzle.
Snapshot
- Course/Lab: AE 4699 CFD Lab
- Case type: Compressible internal flow (convergent-divergent nozzle)
- Solver: ANSYS Fluent
- Primary focus: Choking behavior, Mach trend, and pressure trend consistency
Mission and setup
- Build a clean compressible-flow case with explicit pressure inlet/outlet conditions.
- Confirm expected nozzle physics:
- Flow accelerates through the throat
- Throat reaches choking condition
- Diverging section trends to supersonic exit
- Use contour interpretation to verify physical consistency before reporting.
What I executed
- Defined stagnation-pressure inlet and static-pressure outlet target case.
- Solved and post-processed Mach and static-pressure contours.
- Reviewed field behavior against isentropic nozzle expectations.
- Structured results in a lab-report format for fast review.
Results and engineering takeaways
- Choked behavior observed at the throat with monotonic acceleration downstream.
- Mach contour indicates smooth supersonic development toward the exit.
- Static-pressure field drops from inlet to throat and continues downstream as expected.
- Case reinforces the value of trend-level verification before deeper design claims.
Validation and verification notes
- Compared contour trends to expected 1D compressible-flow behavior.
- Checked for non-physical shocks/artifacts in the baseline outlet-pressure case.
- Confirmed pressure and Mach trends remain internally consistent across field views.
Reproducibility notes
- Reusable slide/report structure keeps setup and interpretation standardized.
- Boundary-condition values documented with explicit units and reference conventions.
- Output visuals captured in a fixed sequence for side-by-side rerun comparison.