cfd-validationlisted

Use when you must validate a computational fluid dynamics result against authoritative reference data: select the validation case for the flow regime and application (NACA 0012 or NACA 4412 airfoil, ONERA M6 transonic wing, DLR-F6 transport wing-body, flat plate boundary layer), compute the relative error, RMS error and max local error, run a Richardson extrapolation grid convergence check, judge pass or fail against tolerance bands, and estimate validation uncertainty. Produces the validation verdict and a validation report skeleton. Trigger: cfd validation, validation case selection, richardson extrapolation, grid convergence, naca 0012 drag, onera m6, dlr f6, error metrics, validation uncertainty, validation report.
ashfordeOU/aero-agent-skills · ★ 0 · AI & Automation · score 78

Install: claude install-skill ashfordeOU/aero-agent-skills

# CFD Validation (aerodynamics/cfd/cfd-validation) Use when a CFD result must be judged against authoritative reference data before it can be trusted: which reference case to run, which comparison metrics to use, whether the agreement is within the acceptance band, and how to report it. Follows AIAA G-077-1998 (Guide for the Verification and Validation of CFD Simulations) and ASME V&V 20-2009 (Standard for Verification and Validation in CFD and Heat Transfer); see references/vv-guidance.md. ## Domain quick reference - Verification solves the equations right (code and discretization errors); validation solves the right equations (model vs physical reality). This skill covers validation; pair it with cfd-convergence for residual and mesh checks. - Validation compares computed quantities against reference data of known quality and states PASS or FAIL within a tolerance band. It never proves a code, it bounds it for a stated application and condition range. - Case selection by flow regime and application (implemented in select_validation_case): | Flow regime | Application | Reference case | Key reference values | |---|---|---|---| | incompressible | airfoil | NACA 0012 (alt: NACA 4412) | Cd 0.0081 at M 0.30, Re 6e6 (NACA TR 824) | | transonic | wing | ONERA M6 | CL 0.266, CD 0.0163 at M 0.84, Re 11.72e6, alpha 3.06 deg (AGARD-AR-138) | | transonic / transport | wing-body | DLR-F6 | CD ~ 0.0299 at CL 0.5, M 0.75, Re 3e6 (AIAA Drag Prediction Workshop) | | incompres