Investigation of large scale shock movement in transonic flow

Wollblad, Christian; Davidson, Lars; Eriksson, Lars‐Erik

doi:10.1016/j.ijheatfluidflow.2010.02.009

Cited by 8 publications

(5 citation statements)

References 25 publications

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“…The Reynolds number had however to be decreased by a factor of 11.25 to make the computation feasible, giving Re = B l U ∞ /ν ≈ 3.1 × 10 5 . The effects of the flow conditions and the computational setup have been further examined in Wollblad et al (2010). More recently, Brouwer (2016) performed a DNS but at a higher Mach number (0.79 against 0.7 in Bron (2003)) and at an even lower Reynolds number (Re ≈ 1.7 × 10 5 ).…”

Section: Introductionmentioning

confidence: 99%

Investigation of forced shock-induced separation in transonic channel

Goffart,

Tartinville,

Hirsch

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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This paper presents the results of an implicit large-eddy simulation of the transonic flow over a bump. The conditions are chosen such that the configuration reproduces actual turbomachinery flows: a shock wave develops as in a transonic passage and a fluctuating backpressure is imposed to mimic the perturbations coming from a downstream row. The aim of the study is to investigate the influence of the forced conditions on the flow field, with an emphasis on the harmonic component of the turbulent stresses in the recirculation region. Results indicate that all the flow features (shock motion, wall static pressure, separation and reattachment points) respond primarily to the forcing frequency. Phaseaveraging is employed to extract the coherent component of the flow. It is shown that the harmonic turbulent stresses are organized into different structures and are non-negligible with respect to the mean component. KEYWORDSchannel flow, transonic, forced oscillation, turbulence NOMENCLATURE B l bump length [m] δ 0 reference boundary layer thickness [m] ∆ x , ∆ y , ∆ z grid resolution in the streamwise, wall-normal and spanwise direction [m] ν kinematic viscosity [m 2 /s] U ∞ freestream velocity [m/s] Abbreviations CFL Courant-Friedrichs-Lewy DNS Direct Numerical Simulation FFT Fast Fourier Transform (I)LES (Implicit) Large-Eddy Simulation PDF Probability Density Function (U)RANS (Unsteady) Reynolds-Averaged Navier-Stokes WPSD Weighted Power Spectral Density Superscripts + wall unit ..

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Section: Introductionmentioning

confidence: 99%

Investigation of forced shock-induced separation in transonic channel

Goffart,

Tartinville,

Hirsch

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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“…Levy [8] proposed a numerical model for computations of unsteady turbulent flows with separation caused by a shock wave over an airfoil. Recently, advanced numerical simulations have been used for SWBLI in investigations of the transonic flow around airfoils [9,10]. A comprehensive review of recent progress in shock wave/boundary layer interactions research can be found in [11] and a review of unsteady transonic aerodynamics can be found in [12].…”

Section: Introductionmentioning

confidence: 99%

Piv Measurements of Flow Separation Over Laminar Airfoil at Transonic Speeds

Stryczniewicz

Placek

Szczepaniak

2016

Journal of KONES. Powertrain and Transport

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The paper presents results of transonic flow field visualization over a laminar airfoil in high-speed wind tunnel. Quite recently, considerable attention has been paid to experimental investigations of an interaction between the shock and the boundary layer for aerodynamics applications. The purpose of the paper is to investigate development of the flow separation over laminar airfoil at transonic speeds. In a course of presented studies, the Particle Image Velocimetry (PIV) method was used for instantaneous velocity measurements of flow field in the test section of N-3 Institute of Aviation transonic wind tunnel. The object of the research was a laminar airfoil inclined at various angles. The effect of the varying angle of incidence on the flow filed was investigated. The freestream Mach number was 0.7. The results of the PIV measurements were analysed in order to identify the type of the separation from the measured velocity fields. Three forms of separation for low, medium and high angle of incidence was distinguished. The results are in good agreement with theoretical models reported in the literature. The study showed that application of quantitative flow visualisation technique allowed gaining new insights on the complex phenomenon of transonic flow over airfoil. The results of the presented research can be used for better understanding of the mechanism of the flow separation process in transonic flow over airfoils and fluid structure interactions.

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“…Lee [6,42] has proposed the self-excited-feedback model to explain the mechanism, which assumes that the sound wave caused by the free shear layer of the trailing edge travels upstream on the upper surface and forms a feedback together with the shock oscillation, thus leading to an unsteady flow. Transonic buffet is an unstable aerodynamic phenomenon; thus, most of the numerical research is performed for the stationary wing or airfoil [43][44][45][46][47][48][49][50][51][52][53]. Many researchers utilize the unsteady Reynoldsaveraged Navier-Stokes (URANS) methods and combine various turbulence models to simulate transonic buffet flows 4.…”

Section: Introductionmentioning

confidence: 99%

“…Many researchers utilize the unsteady Reynoldsaveraged Navier-Stokes (URANS) methods and combine various turbulence models to simulate transonic buffet flows 4. Other use the detached eddy simulation [47,48], large eddy simulation [49,50], or direct numerical simulation methods [51]. Crouch [52,53] has studied the mechanism of the transonic buffet with the global instability theory.…”

Section: Introductionmentioning

confidence: 99%

The interaction between flutter and buffet in transonic flow

et al. 2015

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This paper presents a kind of nodal-shaped oscillation that is caused by the interaction between flutter and buffet in transonic flow. This response differs from the common limit cycle oscillation that appears in transonic aeroelastic problems. The benchmark active controls technology model with the NACA0012 airfoil is used as the research model. First, both buffet and flutter cases are computed through unsteady Reynolds-averaged Navier-Stokes method and are validated by experimental data. Second, the interaction is found to occur beyond the flutter onset velocity at Mach 0.71. When the pitching angle of a fluttering structure exceeds the buffet onset angle, the highfrequency aerodynamic loads induced by transonic buffet destroy the original flutter model, and then the amplitude of the structure motion decays. When the structural pitching angle is less than the buffet onset angle, the buffet disappears and flutter occurs again. As the process repeats itself, the transonic aeroelastic system displays a nodal-shaped oscillation (divergentdamping-divergent-damping oscillation). Finally, the mechanism of the interaction is discussed by analyzing the energy transportation between the flow and the structure in one cycle of nodal-shaped oscillation, and by observing the variation in the phase-angle difference between the plunging and pitching displacements. In this way, this research provides a new approach to understand flutter suppression.

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Investigation of large scale shock movement in transonic flow

Cited by 8 publications

References 25 publications

Investigation of forced shock-induced separation in transonic channel

Investigation of forced shock-induced separation in transonic channel

Piv Measurements of Flow Separation Over Laminar Airfoil at Transonic Speeds

The interaction between flutter and buffet in transonic flow

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