Dissertation/Thesis Abstract

Aero-Optical Prediction of High-Reynolds Number Flows Using Wall-Modeled Large-Eddy Simulation
by Kamel, Mohammed S., Ph.D., University of Notre Dame, 2017, 129; 13836449
Abstract (Summary)

Reliable prediction of optical wavefront distortions induced by compressible turbulent flow surrounding an aperture is crucial to the development of airborne laser systems. Large-eddy simulation (LES) with a wall model provides a promising high-fidelity simulation method for high-Reynolds-number aero-optical flows by avoiding the severe near-wall resolution requirement. In this study, wall-modeled LES is employed to predict and analyze aero-optical distortions of subsonic and supersonic turbulent boundary layers and subsonic and transonic flows over cylindrical turrets at high Reynolds numbers. The results are compared to experimental measurements and previous results from wall-resolved LES at reduced Reynolds numbers.

For turbulent boundary layers at Mach numbers from 0:5 to 4:3 and Reynolds numbers up to Re&thetas; = 6:9104, reasonable agreement is obtained between numerical predictions and experimental data in terms of the magnitude and structures of optical distortions. The optical statistics are dominated by large-scale flow structures in the outer layer. The density correlations and pre-multiplied power spectra capture the features of large-scale motions whose length scales are comparable to the boundary layer thickness.

Subsonic and transonic flows over a cylindrical turret are simulated under experimental conditions. The subsonic flow aero-optical results show agreement with the experimental data of Gordeyev et al. (AIAA Paper 2005-4657) and previous wall-resolved LES results. For the transonic flow, the simulation accurately predicts the fundamental frequency of the shock-induced pressure fluctuations and harmonics (Vorobiev et al., AIAA Paper 2014-2357). It is found that the piston and tilt components of the optical distortions are highly correlated with the shock-induced pressure oscillations, and the shock motion is clearly identified in the unsteady wavefront, which gives valuable input for the design of adaptive-optics systems synchronized with surface-pressure sensors. The LES data is also employed to provide a better understanding of the underlying physics of the shock-separation interaction.

Indexing (document details)
Advisor:
Commitee:
School: University of Notre Dame
Department: Aerospace and Mechanical Engineering
School Location: United States -- Indiana
Source: DAI-B 80/06(E), Dissertation Abstracts International
Source Type: DISSERTATION
Subjects: Aerospace engineering
Keywords: Aero-optics, Computalional fluid dynamics, High reynolds number, Large-eddy simulation, Les, Wall model
Publication Number: 13836449
ISBN: 978-0-438-83635-8
Copyright © 2019 ProQuest LLC. All rights reserved. Terms and Conditions Privacy Policy Cookie Policy
ProQuest