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| Overview | | Validation Studies | | Rear Wing Analysis | | 3D Optimisation | | Redesign | | Front Wing Design | | Nonuniform Onset Flow |

Easy Steps to NEWPAN Racecar Rear Wing Analysis

Step 1. Import your wing surfaces from CAD into GEMS.
Step 2. Use the customised "Create Wing Grid" function in GEMS to specify chordwise and spanwise grid distributions: create structured wing grids in one easy step.

Step 3. Using the endplate outer profile, and the end sections for the wings where they abut the endplate, provide the trim lines, and optionally also internal grid control lines, necessary to generate the endplate grid.

Step 4. Using the GEMS unstructured grid generator, create the endplate panelling from the trim lines in a couple of mouse clicks. Identify the endplate as being "thin" (double sided).

Step 5. "Cap" the wing elements with unstructured grids.

Admire our completed NEWPAN surface panelling.

Step 6. Specify the wake topology using the customised GEMS dialog; starting wake geometry is created for us.
Step 7. Run NEWPAN directly from GEMS (or from the command line if we prefer). Specify the run setup from the dialog. Watch NEWPAN run in a popup window. Expect a runtime of a few minutes - so we may have time to run to the coffee machine.
Step 8. NEWPAN results are automatically displayed for us in the VIEWPAN post-processor. View streamlines, boundary layer properties, sectional pressures and spanwise loadings.

We probably haven't reached lunchtime yet; catch up on our emails and decide on our priorities for this afternoon:


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