Automated Parametric Analysis of Defect Effects on Flight Dynamics

A process to evaluate the overall performance impact of externally generated defects in the outer mold line or control surfaces of aircraft and missiles is proposed. A state-space model is used to evaluate the system response; aerodynamic loads for system response analyses are calculated from aerodynamic quantities, such as aerodynamic coefficients and stability derivatives, which are determined using computational aerodynamic models. Analysis is automated by upfront parametrization of models. Adaptive mesh refinement (AMR) is used to ensure model quality. Analysis is accelerated using response sensitivity computations and advanced computational aerodynamic methods. A successful Phase I effort demonstrated the numerical strategy for computation of aerodynamic coefficients, stability derivatives, and corresponding flight dynamic response. Prediction accuracy was validated against published test data, recommendations were made for additional validation experiments, process efficiency was documented, the value of parameter sensitivity results was demonstrated, the readiness of state-of-the-art AMR methods for use by nonexpert users was shown, and effective engagement strategy development was demonstrated. The planned Phase II effort will mature the process into a functional tool with a graphical user interface and user documentation. Wind tunnel validation experiments will be conducted, and the results will be used to further validate response predictions. The robustness of the overall process will be tested in a wider range of Mach numbers. The final software will provide a user-focused workflow enabling efficient definition of parametric defect sets, calculation of aerodynamic coefficients and stability derivatives, and demonstration of defect impact on vehicle performance.