Boundary-layer instabilities of a finned cone at Mach = 6, Re = 8.4 × 106 [m-1], 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 RefinementWavepacket Tracking (AMR-WPT) are presented. One of the major findings of the work includes identification of a dominant three-dimensional vortex instability occurring at ≈ 250 kHz that correlates well with experimental measurements of transition onset. With the exception ofLST, all of the higher-fidelity linearmethods considered in thisworkwere 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.
|Original language||English (US)|
|Title of host publication||AIAA AVIATION 2022 Forum|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2022|
|Event||AIAA AVIATION 2022 Forum - Chicago, United States|
Duration: Jun 27 2022 → Jul 1 2022
|Name||AIAA AVIATION 2022 Forum|
|Conference||AIAA AVIATION 2022 Forum|
|Period||6/27/22 → 7/1/22|
Bibliographical noteFunding Information:
The authors wish to acknowledge Drew Turbeville and Steve Schneider for providing the experimental data used in this work. D.B.A, N.P.B, and B.M.W were supported by the Office of Naval Research under NAVSEA contract number N00024-13-D-6400 (PO: Dr. Eric Marineau). O.K. and T.C. were supported by The Boeing Company through the Strategic Research and Development Relationship Agreement CT-BA-GTA-1 and through the Office of Naval Research via grant N00014-21-1-2158. They also acknowledge support of the Natural Sciences and Engineering Research Council of Canada via the Postgraduate Doctoral Scholarship (PGSD3-532522-2019). J.W.N. was supported by ONR grant N00014-19-1-2037. CB and VR gratefully acknowledge funding support provided by ACCESS with grant number 80NSSC21K1117 and Dr. Claudia Meyer as Program Manager and by the Office of Naval Research under contract N00014-19-1-2223 with Dr. Eric Marineau as Program Manager. A.L.K. and G.V.C. were supported by the Air Force Office of Scientific Research under grant number FA9550-21-1-0106 and the Office of Naval Research under grant number N00014-19-1-2037. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the AFOSR, the ONR, or the U.S. Government.
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