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Automated Parametric Analysis of Defect Effects on Flight Dynamics
Phone: (703) 225-7451
Phone: (858) 480-2028
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 will be used to evaluate the system response; aerodynamic loads for system response analyses will be calculated from aerodynamic quantities, such as aerodynamic coefficients and stability derivatives, which will be determined using computational aerodynamic models. Analysis will be automated by upfront parametrization of models. Adaptive mesh refinement (AMR) will be used to ensure model quality. Analysis will be accelerated using response sensitivity computations and frequency-domain aerodynamic methods. A successful Phase I effort will demonstrate the numerical strategy for computation of aerodynamic coefficients, stability derivatives, and corresponding flight dynamic response. Prediction accuracy will be validated against published test data, recommendations will be made for additional validation experiments, process efficiency will be documented, the value of parameter sensitivity results will be demonstrated, the readiness of state-of-the-art AMR methods for use by nonexpert users will be shown, and effective engagement strategy development will be demonstrated. The planned Phase II effort will mature the process into a functional tool with a graphical user interface and user documentation. Either wind tunnel or free-flight validation experiments, as recommended during Phase I, will be conducted, and the results will be used to validate response predictions. Any AMR robustness challenges identified in Phase I will be addressed during Phase II so that the software can be used by engineers who are not CFD experts. The final software will provide a user-focused workflow enabling efficient definition of parametric defect sets, calculation of aerodynamic derivatives, and demonstration of defect impact on flight dynamics.
* Information listed above is at the time of submission. *