CFD-Based Prediction of Dynamic Stability Derivatives for the CRM at Low-Speed

This study presents CFD predictions of the static and dynamic aerodynamic behavior of the NASA/Boeing Common Research Model (CRM) for the Second AIAA Stability and Control Prediction Workshop (SCPW2). The CREATE-AV/Kestrel solver is used with a family of systematically refined unstructured grids ranging from 23 to 231 million cells to evaluate mesh sensitivity and to compute both steady and forced-motion aerodynamic responses at low speed (Mach 0.0358, Reynolds number 1.4×10⁵). The Coarse, Medium, and Fine meshes share the same overall topology, whereas the ExtraFine mesh is produced from the Fine grid through two targeted refinements: a modest increase in leading-edge resolution and, more importantly, concentrated clustering in the wing–body junction region. This local refinement markedly enhances the prediction of separation onset, inboard vortex formation, and post-stall flow evolution. Static results across angles of attack from 4 to 24 degrees illustrate the transition from attached flow to deep stall, with the ExtraFine grid showing clearer resolution of vortex structures and sharper aerodynamic trends. Dynamic pitch, roll, and yaw simulations generate time-resolved aerodynamic loads from which damping derivatives are extracted using both regression-based and extremum-rate methods. Overall, the results provide a high-fidelity numerical baseline that will support upcoming experimental comparisons and serve as a foundation for future reduced-order modeling developments.