Summary of a Mach 2.5 Shock Wave Turbulent Boundary Layer Interaction Experiment in a Circular Test Section

Sasson, Jonathan; Davis, David O.; Barnhart, Paul J.; Reising, Heath H.

doi:10.2514/6.2023-0442

Cited by 4 publications

(11 citation statements)

References 10 publications

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“…For the 13.5 deg and 16 deg halfangles, the interaction was stronger and the flow separated from the tunnel wall. Swept (asymmetric) interactions were obtained by a parallel offset of the shock generator from the centerline [28,32,[34][35][36]. Two shock generator offsets from the centerline, R/4 = 2.13 cm and R/3 = 2.83 cm, were considered.…”

Section: Methodsmentioning

confidence: 99%

“…A wall-resolved implicit large-eddy simulation (ILES) of the Mach 2.5 experiment with shock generator radius and cone half angle of 2.5 cm (made dimensionless with the test section diameter, r SG = 0.147) and 16 deg, respectively, and shock generator offset from the centerline of R/3 = D/6 = 2.83 cm (asymmetric case) was carried out. Out of the cases considered in the experiments [28,32,35], this case has the largest crossflow component and is most interesting with respect to the unsteady flow physics. The results obtained from the present simulation are compared with those from an earlier simulation by Mosele et al [37] for a corresponding axisymmetric case (shock generator aligned with the test section centerline, same shock generator radius and cone half angle).…”

Section: Overview Of Simulationsmentioning

confidence: 99%

“…The laminar and turbulent Prandtl numbers were Pr = 0.72 and Pr T = 0.9 and the freestream Mach number was 2.5. The reference Reynolds number for the simulations was Re D = 4 × 10 5 and, thus, 10 times smaller than in the experiments [28,32,35]. The dimensionless computational time-step for the precursor RANS calculation was ∆t = 0.005.…”

Section: Governing Equations and Discretizationmentioning

confidence: 99%

“…Such interactions are not only highly relevant for circular inlet flows but also help avoid issues faced in SBLI experiments in rectangular test sections [29,30], such as corner effects, which are exacerbated in the presence of crossflow and 3D flow features. To date, only two asymmetric constant-strength shock interactions (i.e., shock-generator cone displaced from centerline) in axisymmetric test sections have been performed [31,32] and no accompanying high-fidelity simulations exist. Unfortunately, the experiment by Chou [31] was not included in the computational fluid dynamics (CFD) validation assessment by Settles and Dodson [33].…”

Section: Introductionmentioning

confidence: 99%

“…Recent Mach 2.5 axisymmetric SBLI experiments conducted at the NASA Glenn Research Center by Davis, Sasson, Reising and others [28,32,[34][35][36] were nominally symmetric in the azimuthal direction, which eliminated geometric complexity and also solved the finite span effect problems encountered in flat-plate SBLI experiments. In addition, the experiment's nominal symmetry in the azimuthal direction renders it more suitable for simulations.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of Asymmetric Mach 2.5 Turbulent Shock Wave Boundary Layer Interaction

Groß

Slater

2023

Aerospace

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Supersonic shock wave boundary layer interactions are common to inlet flows of supersonic and hypersonic vehicles. This paper reports on wall-resolved implicit large-eddy simulations of a canonical Mach 2.5 turbulent shock wave boundary layer interaction experiment at the NASA Glenn Research Center. The boundary layer upstream of the interaction was nominally axisymmetric and two-dimensional. A conical centerbody with a 16 deg half-angle and a maximum radius of 0.147D of the test section diameter was employed to generate a conical shock wave, where D is the test section diameter. Asymmetric (swept) interactions were obtained by displacing the shock generator away from the test section centerline. The present simulation is for a shock generator displacement of D/6. Results from the asymmetric simulation are compared with results from an earlier simulation of a corresponding axisymmetric interaction. The experimental Reynolds number based on test section diameter was ReD=4×106. For the simulations, the Reynolds number was lowered to ReD=4×105 to keep the computational expense of the simulations within limits. Compared to the axisymmetric interaction, the streamwise extent of the separation varies considerably in the azimuthal direction for the asymmetric interaction. The separation is strongest at the azimuthal location that is closest to the shock generator. The streamwise extent of the separated flow regions is noticeably reduced and substantial crossflow is observed between the locations that are closest and farthest from the shock generator. A Fourier analysis of the unsteady flow data indicates low-frequency content for the separated region that is closest to the shock generator. Away from this region, with increasing sweep angle and cross-flow, the low-frequency content is diminished. A proper orthogonal decomposition captures spanwise coherent structures for the more two-dimensional parts of the interaction.

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