Advancing the Multi-Solver Paradigm for Overset CFD Toward Heterogeneous Architectures

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dc.contributor.advisorBaeder, Jamesen_US
dc.contributor.authorJude, Dylan Pen_US
dc.contributor.departmentAerospace Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.date.accessioned2019-10-01T05:35:13Z
dc.date.available2019-10-01T05:35:13Z
dc.date.issued2019en_US
dc.description.abstractA multi-solver, overset, computational fluid dynamics framework is developed for efficient, large-scale simulation of rotorcraft problems. Two primary features distinguish the developed framework from the current state of the art. First, the framework is designed for heterogeneous compute architectures, making use of both traditional codes run on the Central Processing Unit (CPU) as well as codes run on the Graphics Processing Unit (GPU). Second, a framework-level implementation of the Generalized Minimal Residual linear solver is used to consider all meshes from all solvers in a single linear system. The developed GPU flow solver and framework are validated against conventional implementations, achieving a 5.35× speedup for a single GPU compared to 24 CPU cores. Similarly, the overset linear solver is compared to traditional techniques, demonstrating the same convergence order can be achieved using as few as half the number of iterations. Applications of the developed methods are organized into two chapters. First, the heterogeneous, overset framework is applied to a notional helicopter configuration based on the ROBIN wind tunnel experiments. A tail rotor and hub are added to create a challenging case representative of a realistic, full-rotorcraft simulation. Interactional aerodynamics between the different components are reviewed in detail. The second application chapter focuses on performance of the overset linear solver for unsteady applications. The GPU solver is used along with an unstructured code to simulate laminar flow over a sphere as well as laminar coaxial rotors designed for a Mars helicopter. In all results, the overset linear solver out-performs the traditional, de-coupled approach. Conclusions drawn from both the full-rotorcraft and overset linear solver simulations can have a significant impact on improving modeling of complex rotorcraft aerodynamics.en_US
dc.identifierhttps://doi.org/10.13016/kcec-84kk
dc.identifier.urihttp://hdl.handle.net/1903/25105
dc.language.isoenen_US
dc.subject.pqcontrolledAerospace engineeringen_US
dc.subject.pquncontrolledComputational Fluid Dynamicsen_US
dc.subject.pquncontrolledGPUen_US
dc.subject.pquncontrolledHeterogeneousen_US
dc.subject.pquncontrolledInteractional Aerodynamicsen_US
dc.subject.pquncontrolledOverseten_US
dc.subject.pquncontrolledRotorcraften_US
dc.titleAdvancing the Multi-Solver Paradigm for Overset CFD Toward Heterogeneous Architecturesen_US
dc.typeDissertationen_US

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