Committee Chair

Sreenivas, Kidambi

Committee Member

Webster, Robert S.; Karman Jr., Steve L.

Department

Dept. of Computational Engineering

College

College of Engineering and Computer Science

Publisher

University of Tennessee at Chattanooga

Place of Publication

Chattanooga (Tenn.)

Abstract

The study uses computational methods to simulate fluid flow on the NASA ROBIN helicopter model and on a simplified rotor geometry previously tested at Mississippi State. The ROBIN model and the rotor are run using an unstructured grid. Results from the Tenasi flow solver are compared against both simulated and wind tunnel data. Tenasi is an unstructured, Reynolds Averaged Navier-Stokes (RANS) solver developed at the SimCenter: National Center for Computational Engineering, located at the University of Tennessee at Chattanooga. Steady-state results for the isolated ROBIN fuselage and unsteady results for both fuselage and rotor systems are computed. In the unsteady case, relative grid motion of both the rotor disk relative to the fuselage and the cyclic pitching motion of each blade as the rotor turns must be simulated. Thus, each moving component is meshed in its own subdomain, and a nonmatching and sliding interface method is used to compute fluxes across the subdomain boundaries. Testing of the implementation of this method in Tenasi is the primary purpose of the study.

Acknowledgments

Tennessee Higher Education Center of Excellence for Applied Computational Science and Engineering

Degree

M. S.; A thesis submitted to the faculty of the University of Tennessee at Chattanooga in partial fulfillment of the requirements of the degree of Master of Science.

Date

12-2013

Subject

Interpolation

Keyword

RANS; Sliding interfaces; ROBIN; Rotorcraft; Computational fluid dynamics

Discipline

Applied Mathematics | Computational Engineering

Document Type

Masters theses

Extent

xiv, 110 leaves

Language

English

Rights

Under copyright.

License

http://creativecommons.org/licenses/by-nc-sa/3.0/

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