Numerical investigations of turbulent duct flows using wall-modeled large-eddy simulation
Abstract/Contents
- Abstract
- The challenges posed by shock wave-turbulent boundary layer interactions (STBLIs) remain one of the primary considerations in the design and operation of air-breathing hypersonic vehicles. The internal flow within the isolator of a scramjet engine involves a series of coupled STBLIs. In order to study these phenomena, the interaction of a turbulent boundary layer with a shock train in a constant area duct (STCAD) is used as a model problem. Calculations of a STCAD are performed using wall-modeled Large-Eddy Simulation (WMLES). This approach reduces the computational cost of a simulation by modeling the inner portion of the boundary layer and thereby enables the calculation of high Reynolds number flows. The equilibrium formulation of the wall-model, which neglects the pressure gradient and convective terms in the thin boundary layer equations (TBLEs), is evaluated for a class of flows where the non-equilibrium characteristics are primarily exhibited outside of the wall-modeled region. Several modifications to the framework of the WMLES are also developed and tested in order to improve predictions for turbulent, non-circular duct flows. Results from calculations of a STCAD at lower Reynolds number are compared with previous wall-resolved LES investigations to establish confidence in the approach. The WMLES is then applied to a STCAD at the higher Reynolds number conditions from experiments where wall-resolved calculations were prohibitively expensive. A parameter study related to the physical characteristics of the interaction is performed to address the uncertainty created by the lack of experimental data with respect to the side wall boundary layers. The equilibrium WMLES is shown to provide accurate predictions in comparison with the experimental data measured in the spanwise center plane. The physics of the STCAD are shown to be strongly dependent on the three-dimensional confinement of the mean flow by the boundary layer as well as the pressure ratio across the interaction. Further studies explore the effects that the side wall boundary layers and variations in the Reynolds number have on the properties of the interaction. An investigation into the potential applicability of a reduced-order model to predict the general trends exhibited by the three-dimensional STCAD is also conducted.
Description
| Type of resource | text |
|---|---|
| Form | electronic; electronic resource; remote |
| Extent | 1 online resource. |
| Publication date | 2015 |
| Issuance | monographic |
| Language | English |
Creators/Contributors
| Associated with | Vane, Zachary Phillips |
|---|---|
| Associated with | Stanford University, Department of Aeronautics and Astronautics. |
| Primary advisor | Lele, Sanjiva K. (Sanjiva Keshava), 1958- |
| Thesis advisor | Lele, Sanjiva K. (Sanjiva Keshava), 1958- |
| Thesis advisor | Alonso, Juan José, 1968- |
| Thesis advisor | MacCormack, R. W. (Robert William), 1940- |
| Advisor | Alonso, Juan José, 1968- |
| Advisor | MacCormack, R. W. (Robert William), 1940- |
Subjects
| Genre | Theses |
|---|
Bibliographic information
| Statement of responsibility | Zachary Phillips Vane. |
|---|---|
| Note | Submitted to the Department of Aeronautics and Astronautics. |
| Thesis | Thesis (Ph.D.)--Stanford University, 2015. |
| Location | electronic resource |
Access conditions
- Copyright
- © 2015 by Zachary Phillips Vane
- License
- This work is licensed under a Creative Commons Attribution Non Commercial 3.0 Unported license (CC BY-NC).
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