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Please use this identifier to cite or link to this item: http://hdl.handle.net/1807/32758

Title: Stability-constrained Aerodynamic Shape Optimization with Applications to Flying Wings
Authors: Mader, Charles
Advisor: Martins, Joaquim R. R. A.
Department: Aerospace Science and Engineering
Keywords: optimization
design optimization
aerodynamic shape optimization
flying wings
aircraft design
Issue Date: 30-Aug-2012
Abstract: A set of techniques is developed that allows the incorporation of flight dynamics metrics as an additional discipline in a high-fidelity aerodynamic optimization. Specifically, techniques for including static stability constraints and handling qualities constraints in a high-fidelity aerodynamic optimization are demonstrated. These constraints are developed from stability derivative information calculated using high-fidelity computational fluid dynamics (CFD). Two techniques are explored for computing the stability derivatives from CFD. One technique uses an automatic differentiation adjoint technique (ADjoint) to efficiently and accurately compute a full set of static and dynamic stability derivatives from a single steady solution. The other technique uses a linear regression method to compute the stability derivatives from a quasi-unsteady time-spectral CFD solution, allowing for the computation of static, dynamic and transient stability derivatives. Based on the characteristics of the two methods, the time-spectral technique is selected for further development, incorporated into an optimization framework, and used to conduct stability-constrained aerodynamic optimization. This stability-constrained optimization framework is then used to conduct an optimization study of a flying wing configuration. This study shows that stability constraints have a significant impact on the optimal design of flying wings and that, while static stability constraints can often be satisfied by modifying the airfoil profiles of the wing, dynamic stability constraints can require a significant change in the planform of the aircraft in order for the constraints to be satisfied.
URI: http://hdl.handle.net/1807/32758
Appears in Collections:Doctoral

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