Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Arisman, C. J.; Johansen, C. T.; Bathel, B. F.; Danehy, Paul M.

doi:10.2514/1.j055125

Cited by 2 publications

(5 citation statements)

References 31 publications

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“…The shock wave angle predicted by the full energy formulation is β s ∼ 7 • , while the angle predicted by the reduced energy formulation is β s ∼ 6.3 • . The angle prediction of the full energy formulation is very close to the one predicted by OpenFOAM [71], which is β a ∼ 7.2 • , while the reduced energy formulation underpredicts this value. The smaller shock wave angle predicted by the reduced energy formulation is the reason behind the higher Mach number predicted in the post-shock region.…”

Section: D Mach 10 Oblique Shock Problemsupporting

confidence: 56%

“…Next, the results of a 2D Mach 6 flat plate [70] problem with detailed mesh convergence study, are presented. A Mach 10 NASA wedge test case [71] is shown, followed by the Mach 17 flow over a cylinder problem [72] to investigate the instabilities, namely "Carbuncle problem" [73], encountered when traditional CAU DC operator, DC 1 , is used. An alternative definition of DC operator, DC 2 , that alleviates this problem, is proposed.…”

Section: Numerical Resultsmentioning

confidence: 99%

“…The Mach contours for full and reduced energy formulations are shown in Figure 13a and in Figure 13b respectively. Figure 14 shows the Mach profile at x = 0.106 [m] where the results are compared with simulation results using OpenFOAM [71]. The results from the full energy formulation show very good agreement.…”

Section: D Mach 10 Oblique Shock Problemmentioning

confidence: 96%

“…The smaller shock wave angle predicted by the reduced energy formulation is the reason behind the higher Mach number predicted in the post-shock region. The velocity profiles in the boundary layer at four different locations, Figure 14: Mach profile at x = 0.106 [m] obtained using both formulations is compared with numerical results of [71] for the Mach 9.7 oblique shock.…”

Section: D Mach 10 Oblique Shock Problemmentioning

confidence: 99%

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Stabilized methods for high-speed compressible flows: toward hypersonic simulations

et al. 2021

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A stabilized finite element framework for high-speed compressible flows is presented. The Streamline-Upwind/Petrov-Galerkin formulation augmented with discontinuity-capturing (DC) are the main constituents of the framework that enable accurate, efficient, and stable simulations in this flow regime. Full-and reduced-energy formulations are employed for this class of flow problems and their relative accuracy is assessed. In addition, a recently developed DC formulation is presented and is shown to be particularly well suited for hypersonic flows. Several verification and validation cases, ranging from 1D to 3D flows and supersonic to the hypersonic regimes, show the excellent performance of the proposed framework and set the stage for its deployment on more advanced applications.

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Section: D Mach 10 Oblique Shock Problemsupporting

confidence: 56%

Section: Numerical Resultsmentioning

confidence: 99%

Section: D Mach 10 Oblique Shock Problemmentioning

confidence: 96%

Section: D Mach 10 Oblique Shock Problemmentioning

confidence: 99%

See 2 more Smart Citations

Stabilized methods for high-speed compressible flows: toward hypersonic simulations

et al. 2021

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“…The flow is modeled using an explicit, second-order Roe-FDS method where the gradient is estimated using Green-Gauss Node-based technique (ANSYS, 2013). The ANSYS Fluent has two solver schemes, AUSM and Roe-FDS; however, the Roe-FDS scheme is chosen to compute the flux vectors without an oscillatory solution at the flow discontinuities according to Arisman et al (2015).…”

Section: D Axisymmetric Modelmentioning

confidence: 99%

Blast load simulation using conical shock tube systems

Ismail

Ezzeldin

El‐Dakhakhni

et al. 2019

International Journal of Protective Structures

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With the increased frequency of accidental and deliberate explosions, evaluating the response of civil infrastructure systems to blast loading has been attracting the interests of the research and regulatory communities. However, with the high cost and complex safety and logistical issues associated with field explosives testing, North American blast-resistant construction standards (e.g. ASCE 59-11 and CSA S850-12) recommend the use of shock tubes to simulate blast loads and evaluate relevant structural response. This study first aims at developing a simplified two-dimensional axisymmetric shock tube model, implemented in ANSYS Fluent, a computational fluid dynamics software, and then validating the model using the classical Sod’s shock tube problem solution, as well as available shock tube experimental test results. Subsequently, the developed model is compared to a more complex three-dimensional model and the results show that there is negligible difference between the two models for axisymmetric shock tube performance simulation; however, the three-dimensional model is necessary to simulate non-axisymmetric shock tubes. Following the model validation, extensive analyses are performed to evaluate the influences of shock tube design parameters (e.g. the driver section pressure and length and the expansion section length) on blast wave characteristics to facilitate a shock tube design that would generate shock waves similar to those experienced by civil infrastructure components under blast loads. The results show that the peak reflected pressure increases as the driver pressure increases, while a decrease in the expansion length increases the peak reflected pressure. In addition, the positive phase duration increases as both the driver length and expansion length are increased. Finally, the developed two-dimensional axisymmetric model is used to optimize the dimensions of a physical large-scale conical shock tube system constructed for civil infrastructure component blast response evaluation applications. The capabilities of such shock tube system are further investigated by correlating its design parameters to a range of explosion threats identified by different hemispherical TNT charge weight and distance scenarios.

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Investigation of Gas Seeding for Planar Laser-Induced Fluorescence in Hypersonic Boundary Layers

Cited by 2 publications

References 31 publications

Stabilized methods for high-speed compressible flows: toward hypersonic simulations

Stabilized methods for high-speed compressible flows: toward hypersonic simulations

Blast load simulation using conical shock tube systems

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