Theses and Dissertations

Title

RANS and DES Computations for a Three-Dimensional Wing with ICE Accretion

Author

Prasad Mogili

Issuing Body

Mississippi State University

Advisor

Thompson, David S.

Committee Member

Bridges, David H.

Committee Member

Cinnella, Pasquale

Date of Degree

1-1-2004

Document Type

Graduate Thesis - Open Access

Major

Aerospace Engineering

Degree Name

Master of Science

College

James Worth Bagley College of Engineering

Department

Department of Aerospace Engineering

Abstract

A computational investigation was performed to assess the effectiveness of Detached-Eddy Simulation (DES) as a tool for predicting icing effects. The AVUS code was employed to compute solutions for an iced wing configuration using DES and steady-state Reynolds Averaged Navier-Stokes (RANS) equation methodologies. The model wing was an extruded GLC305/944-ice shape section with a rectangular planform. Unstructured grids were generated using VGRID/GRIDTOOL. The one-equation Spalart-Allmaras turbulence model was used for all steady state RANS and DES computations. The numerical results were evaluated by comparison with experimental data. RANS solutions significantly under-predicted the lift and drag even after mesh refinement. The time-averaged DES computations showed some improvement in lift and drag coefficients, when compared to experimental data near stall at a 6 deg angle of attack. No significant improvement was observed at lower angles of attack. The DES computations were determined to be valid, since significant changes in the flow field were not observed after both mesh refinement and time step refinement.

URI

https://hdl.handle.net/11668/20331

Comments

DES||Iced aircraft wing||RANS

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