Navier-Stokes Calculations of Transonic Flows Past Cavities

Srinivasan, S.; Baysal, Oktay

doi:10.1115/1.2909506

Cited by 28 publications

(11 citation statements)

References 10 publications

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“…Kubotskii and Tarn 38 Ashcroft et al 39 Moon et al 3 Shieh and Morris 61 Slirnon 4 Jacob et al 25 Shieh and Morris 5 Shieh and Morris 40 Colonius et al 53 Dougherty et al 42 Fuglsang and Cain 43 Srinivasan 63 Venkatapathy et al 47 Srinivasan and Bay sal 15 Atwood 41 Tu 76 Suhs 50 Shih et al 79 Kirn and Chokani 68 Zharig 48 Baysal and Stallings 72 Stanek et al 77 Rizzetta 49 Arunajatesan et al 52 Tarn et al 51 ' 75 Sinha et al 44 Gorski et al 45 Baysal 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 2D 3D 2D 3D 2D,3D 3D 3D 2D 2D 2D 2D 3D 3D 3D 2D 3D 3D 2D 3D Same…”

Section: Key For Thementioning

confidence: 97%

“…In the literature though, one can find vastly different values reported. 15 Recently, Tracy and Plentovich 16 and Raman et al 17 have concluded that the disagreement found in the literature stems from the dependence of the cavity flow type on Mach number For open cavities and cavities operating in the shearlayer mode, empirical formulae exist for predicting the frequency of oscillation. For deeper cavities, the natural frequency of the cavity, i.e., acoustic depth modes, are observed.…”

Section: Characterization Of Cavity Flowmentioning

confidence: 98%

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An overview of computational aeroacoustic techniques applied to cavity noise prediction

Grace

2001

39th Aerospace Sciences Meeting and Exhibit

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This report contains a summary of recent advances in the development of computational aeroacoustic methods for predicting the vibration and acoustics associated with grazing flow past cavities. The applications for which this flow field applies vary greatly and thus many Mach number regimes and cavity geometries are discussed. In addition to the computational developments, recent experimental studies are discussed. The results of many of these experiments can be used for validation of present and future prediction tools.

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Section: Key For Thementioning

confidence: 97%

Section: Characterization Of Cavity Flowmentioning

confidence: 98%

An overview of computational aeroacoustic techniques applied to cavity noise prediction

Grace

2001

39th Aerospace Sciences Meeting and Exhibit

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“…Early studies of cavity flows using computational fluid dynamics (CFD) focused on the use of Reynolds-averaged Navier-Stokes (RANS) equations in conjunction with various turbulence closures. Most applications of unsteady RANS (URANS) to cavity flows have employed algebraic turbulence models, especially different versions of the Baldwin-Lomax models [31], due to their simplicity [32,33]. However, such simple eddy viscosity models are not able to predict the turbulent cavity-flow field [34], and investigations with more advanced turbulence models such as the two-equation k-" and k-!…”

Section: A Experimental Studiesmentioning

confidence: 98%

Assessment of Passive Flow Control for Transonic Cavity Flow Using Detached-Eddy Simulation

Lawson

Barakos

2009

Journal of Aircraft

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The implementation of internal store carriage on stealthy military aircraft has accelerated research into transonic cavity flows. Depending on the freestream Mach number and the cavity dimensions, flows inside cavities can become unsteady, threatening the structural integrity of the cavity and its contents (e.g., stores, avionics, etc.). Below a critical length-to-depth ratio, the shear layer formed along the cavity mouth has enough energy to span across the opening. This shear layer impacts the downstream cavity corner and the generated acoustic disturbances propagate upstream, causing further instabilities near the cavity front. Consequently, a self-sustained feedback loop is established. This extreme flow environment calls for flow control ideas aiming to pacify the cavity by breaking the feedback loop and controlling the breakdown of the shear layer. This is the objective of the present work, which aims to assess changes of the cavity geometry and their effect on the resulting flow using detached-eddy simulation. For the cases computed in this work, quantitative and qualitative agreement with experimental data has been obtained. All of the devices tested achieved similar reductions in overall sound pressure level in the rear half of the cavity; however, a slanted aft wall provided the largest noise reduction in the front half of the cavity. Nomenclature A = wall area, m 2 a i t = temporal eigenfunctions C F = force coefficient D = cavity depth, m F, G, H = spatial flux vectors in Navier-Stokes equations f = frequency, Hz L = cavity length, m N = number of snapshots for proper orthogonal decomposition p = pressure, Pa p 0 = unsteady pressure, Pa Q = unsteady terms in Navier-Stokes equations q 1 = freestream dynamic pressure ( 1 2 1 U 2 1 ), Pa Re = Reynolds number Re L = Reynolds number based on cavity length L S = symmetric components of the velocity gradient tensor [Eq. (7)] S = source vector in Navier-Stokes equations [Eq. (1)] T Rossiter1 = time period of the lowest Rossiter mode, s t = time, s u = velocity, m=s x, y, z = Cartesian coordinates, m i = matrix eigenvalues = density, kg=m 3 i x = spatial eigenfunctions = antisymmetric component of the velocity gradient tensor Subscripts rms = root mean square m = mean quantity 1 = freestream value Superscripts inv = inviscid term vis = viscous term

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“…The flow field features boundary layer separation, shear layer instability, vortex flow, acoustics radiation, shock/expansion wave and shock-boundarylayer interactions, and self-sustained pressure oscillations. The co-presence of and interaction among these features in such a simple configuration and their potential hazardous effects on the performance, integrity, and stability of the vehicles present a challenging problem and have stimulated extensive experimental, analytical, 8,9,24,[37][38][39][40] and computational [41][42][43][44][45][46][47][48][49][50][51][52][53][54][55][56][57][58] investigations over the years. These studies largely concentrated on mean static-pressure distributions and/or unsteady-pressure spectra in cavities.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on the Mechanism of Flow-Type Changes in Supersonic Cavity Flows.

Zhang

Morishita

Okunuki

et al. 2002

Trans. Japan Soc. Aero. S Sci.

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Compressible flows over cavities with a series value of length-to-depth ratio (L/D) were investigated experimentally, with the objective being to elucidate the mechanism of the transition of types of cavity flows as their L/D increases or decreases. For open-type cavity flows, the freedom of backflow inside the cavity is found to be crucial in smoothing out adverse pressure gradient. The spreading of the shear layer and its gradual approach toward the cavity floor as L/D increases tend to suppress the freedom of backflow, causing the cavity flow to change from the open-type to the transitional-type. For closed-type cavity flows, the finite thickness of the upstream boundary layer leads to the presence of three kinds of characteristic lengths that correspond to the recirculation region, the deflection of the main flow and the recovery or the abrupt rise of the pressure, respectively. The compression fans at the foot of the impingement and the exit shock waves will approach each other well in advance of the possible merge of the vertices of the conventionally defined separation and recompression wakes. As the L/D of a closed cavity decreases, the reattached boundary layer on the mid-portion of the cavity floor will have less developing distance, thus it will be more susceptible to adverse pressure gradient and prone to separation. For the present two-dimensional cavity models, the critical values of L/D were found to be about 10 and 14 for the transition of cavity flows from the open-to the transitional-type and from the transitionalto the closed-type, respectively. The sum of the pressure lengths at the front and rear wakes agrees remarkably well with the second critical L/D.

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Navier-Stokes Calculations of Transonic Flows Past Cavities

Cited by 28 publications

References 10 publications

An overview of computational aeroacoustic techniques applied to cavity noise prediction

An overview of computational aeroacoustic techniques applied to cavity noise prediction

Assessment of Passive Flow Control for Transonic Cavity Flow Using Detached-Eddy Simulation

Experimental Investigation on the Mechanism of Flow-Type Changes in Supersonic Cavity Flows.

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