Development of three-dimensional turbulent separation in the neighborhood of incident crossing shock waves

Derunov, E. K.; Zheltovodov, A. A.; Maksimov, A. I.

doi:10.1134/s0869864308010034

Cited by 9 publications

(18 citation statements)

References 19 publications

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“…The conical bow shocks induced by the forebodies are shown to merge and re §ect in a complex 3D manner between the bodies and on the plate. Their structure di¨ers markedly from the earlier predictions [3] that employed the Euler equations, due to the emergence of 3D secondary §ows and separation zones in the boundary layer on the plate and bodies£ surfaces described in detail earlier in accordance with the experiments [2,3]. Emerging separation and attachment zones and their interaction with a basic ¢inviscid£ shock wave structure change the §ow¦eld signi¦cantly (further discussion of Fig.…”

Section: Discussion Of Predictions and Comparison Of Measurements Witsupporting

confidence: 62%

Numerical prediction of three-dimensional shock-induced turbulent flow separation surrounding bodies of revolution adjacent to a flat surface

Grosvenor

Zheltovodov

Derunov

2012

Progress in Flight Physics

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Numerical predictions of complex three-dimensional (3D) shock wave / turbulent boundary layer interactions (SWTBLI) are presented. The con¦guration studied is a set of two identical cylindrical bodies with conically shaped noses aligned parallel to a Mach 4 stream, adjacent to a §at plate. A series of distances between the bodies are analyzed to test ability of the numerical algorithms employed to capture complex 3D turbulent separation phenomena observed in experiments conducted at the Khristianovich Institute of Theoretical and Applied Mechanics. The numerical scheme employed solves the Reynolds Averaged Navier Stokes (RANS) equations, and turbulence closure is provided by the low Reynolds number SpalartAllmaras one-equation model. Among other areas of concentration discussed herein are the properties of the computational grid required to capture the §ow physics su©ciently to reproduce the complex boundary layer separation patterns. The value of point-enrichment type adaptation over block-enrichment is demonstrated, and the shock capturing properties of 2nd order central and upwind discretization schemes are compared.

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Section: Discussion Of Predictions and Comparison Of Measurements Witsupporting

confidence: 62%

Numerical prediction of three-dimensional shock-induced turbulent flow separation surrounding bodies of revolution adjacent to a flat surface

Grosvenor

Zheltovodov

Derunov

2012

Progress in Flight Physics

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“…19a. In accordance with [19,20], such asymmetry could be due to small deformations of the test model. The surface static pressure distribution panorama in the interaction region is displayed in Fig.…”

Section: Shock Interactionsupporting

confidence: 72%

“…• and -z/D = 1.8 was presented in [19]. An external boundary of the 3D separated zone beneath the bodies is limited by the primary convergence (separation) lines S 1 , S ′ 1 (see Fig.…”

Section: Resultsmentioning

confidence: 99%

“…2). The experiments were conducted at the freestream Mach number í ∞ = 4.03 and the unit Reynolds number Re 1 = 55 · 10 6 m −1 [19,20]. The adiabatic wall condition was realized in the experiment and the plate turbulent boundary layer thickness was δ = 1.82.0 mm immediately upstream of the impingement location of the generated bow shock waves on the plate.…”

Section: Flow Conditions and Gridmentioning

confidence: 99%

“…The pressure maxima A and B correspond to the symmetric nodes N 1 and N ′ 1 on the plate beneath the bodies B 1 and B 2 , respectively, and the central maximum C arises at the central saddle point C 3 . Details of observations in experimental surface §ow pattern topology and pressure distribution with formed additional symmetric (D, E) and central (M ) maxima are discussed in [19,20].…”

Section: Shock Interactionmentioning

confidence: 99%

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Numerical analysis of three complex three-dimensional shock wave / turbulent boundary layer interaction flows

Grosvenor

Zheltovodov

Matheson

et al. 2013

Progress in Flight Physics

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A set of Reynolds-averaged NavierStokes (RANS) computations with turbulence closure provided by the SpalartAllmaras (SA) model have been carried out for prediction of shock-induced three-dimensional (3D) turbulent separated §ows. The experimental data for di¨erent aerodynamic test con¦gurations have been used for assessing credibility of the numerical method employed. Particularly, shock wave / turbulent boundary layer interactions (SWTBLI) in the vicinity of an asymmetric sharp double-¦n (DF) with di¨erent (7• and 11 • ) de §ection angles mounted on a §at plate and two conically sharp cylindrical bodies at varying interbody distances and nose cone angles 60• and 40• mounted over a §at plate at freestream Mach number 4, as well as a transonic fan stage operating in the near-stall regime are considered. The gas dynamic structure and topology of 3D separated §ows, surface §ow patterns, and pressure distributions as well as body aerodynamic force prediction are analyzed. A transonic fan stage operating in the near-stall regime and a possibility of applying §ow control is investigated. High Performance Computing was employed to make high resolution computations of these §ows possible, and advanced 3D visualization techniques were employed in order to improve understanding of the separating §ow phenomena.

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Aerodynamic interference between high-speed slender bodies

2010

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Significant aerodynamic interference can occur between high-speed bodies in close proximity. A complex flowfield develops where shock and expansion waves from a generator body impinge upon the adjacent receiver body. The pressure and flow angularity changes which occur across these disturbances modify the body aerodynamics. The aim of this research is to quantify the aerodynamic interference effects for multi-body configurations and understand the relevant flow physics.The interference aerodynamics for slender bodies in a supersonic flow were investigated through a parametric wind tunnel study. The receiver bodies were finned and un-finned configurations. The effect of lateral and axial body separations, receiver incidence and the strength of the disturbance field were investigated. Measurements included forces and moments, surface pressures and flow visualisations. Supporting computations using steady-state, viscous predictions provided a deeper understanding of the underlying aerodynamics and flow mechanisms. Good agreement was found Many people have contributed to the completion of this research. I would like to take time to thank them. My supervisor David MacManus for his guidance and help throughout. I would especially like to thank him for the many occasions when he took my work home with him to read and provide feedback during the writing process. I would like to acknowledge the financial support of the UK MOD. The investigation which is the subject of this report was initiated by the Air Systems Department Dstl and was carried out under the terms of Contract No RD025 -1962. Additional funding was also provided through an ESPRC CASE award. I would also like to thank Dstl for the release of experimental data which greatly enhanced this research. Trevor Birch for his constant support and guidance throughout. In particular, I would like to thank him for making arrangements for me to undertake two placements at Dstl. These aided my research and I enjoyed my time at Dstl immensely. Moreover, I would like to also thank Ben Shoesmith and Kristian Petterson who gave up alot of their own time in order to assist me. Their help with IMPNS and Cobalt was particularly useful.

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Development of three-dimensional turbulent separation in the neighborhood of incident crossing shock waves

Cited by 9 publications

References 19 publications

Numerical prediction of three-dimensional shock-induced turbulent flow separation surrounding bodies of revolution adjacent to a flat surface

Numerical prediction of three-dimensional shock-induced turbulent flow separation surrounding bodies of revolution adjacent to a flat surface

Numerical analysis of three complex three-dimensional shock wave / turbulent boundary layer interaction flows

Aerodynamic interference between high-speed slender bodies

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