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Assessment of Linear Methods for Analysis of Boundary Layer Instabilities on a Finned Cone at Mach 6

Araya, Daniel and Bitter, Neal and Wheaton, Bradley M. and Kamal, Omar and Colonius, Tim and Knutson, Anthony and Johnson, Heath and Nichols, Joseph and Candler, Graham V. and Russo, Vincenzo and Brehm, Christoph (2022) Assessment of Linear Methods for Analysis of Boundary Layer Instabilities on a Finned Cone at Mach 6. In: AIAA AVIATION 2022 Forum. American Institute of Aeronautics and Astronautics , Reston, VA, Art. No. 2022-3247. ISBN 978-1-62410-635-4.

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Boundary-layer instabilities of a finned cone at Mach = 6, Re = 8.4 x 10⁶ /m, and zero incidence angle are examined using linear stability methods of varying fidelity and maturity. The geometry and laminar flow conditions correspond to experiments conducted at the Boeing Air Force Mach 6 Quiet Tunnel (BAM6QT) at Purdue University. Where possible, a common mean flow is utilized among the stability computations, and comparisons are made along the acreage of the cone where transition is first observed in the experiment. Stability results utilizing Linear Stability Theory (LST), planar Parabolized Stability Equations (planar-PSE), One-Way Navier Stokes (OWNS), forced direct numerical simulation (DNS), and Adaptive Mesh Refinement Wavepacket Tracking (AMR-WPT) are presented. One of the major findings of the work includes identification of a dominant three-dimensional vortex instability occurring at approximately 250 kHz that correlates well with experimental measurements of transition onset. With the exception of LST, all of the higher-fidelity linear methods considered in this work were consistent in predicting the initial growth and general structure of the vortex instability as it evolved downstream. OWNS analysis utilizing randomized wavenumber forcing identified possible nonmodal interactions contributing to the development of this vortex instability. Both forced DNS and AMR-WPT analysis demonstrated the utility of these methods in tracking either linear or nonlinear growth of disturbances. Finally, a new implementation of Input/Output (I/O) analysis is discussed and some of the challenges, opportunities, and development needs for all of the stability methods are presented.

Item Type:Book Section
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Colonius, Tim0000-0003-0326-3909
Additional Information:© 2022 by the American Institute of Aeronautics and Astronautics, Inc. Under the copyright claimed herein, the U.S. Government has a royalty-free license to exercise all rights for Governmental purposes. All other rights are reserved by the copyright owner. Published Online: 20 Jun 2022.
Subject Keywords:Boundary Layer Transition; Parabolized Stability Equations; Direct Numerical Simulation; Adaptive Mesh Refinement; Vortex Structure; Compressible Flow; Air Forces; Boeing; Shape Functions; Singular Value Decomposition
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AIAA Paper2022-3247
Record Number:CaltechAUTHORS:20220708-930729800
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Official Citation:Daniel Araya, Neal Bitter, Bradley M. Wheaton, Omar Kamal, Tim Colonius, Anthony Knutson, Heath Johnson, Joseph Nichols, Graham V. Candler, Vincenzo Russo and Christoph Brehm. "Assessment of Linear Methods for Analysis of Boundary Layer Instabilities on a Finned Cone at Mach 6," AIAA 2022-3247. AIAA AVIATION 2022 Forum. June 2022; DOI: 10.2514/6.2022-3247
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:115433
Deposited By: Tony Diaz
Deposited On:08 Jul 2022 23:19
Last Modified:08 Jul 2022 23:19

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