Investigation of shock waves interference and associated hysteresis effect at variable-Mach-number upstream flow

Durand, Antoine; Chanetz, Bruno; Benay, R.; Chpoun, A.

doi:10.1007/s00193-003-0177-2

Cited by 6 publications

(4 citation statements)

References 15 publications

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“…A distinction has been made for the data corresponding to a decreasing M 0 and that for an increasing M 0 , but the almost perfect overlap between the two confirms the repeatability, as well as the absence of any measurable hysteresis effects in our experiments. The latter is consistent with past experimental works in noisy facilities [6][7][8]19]. Data shown in Fig.…”

Section: Mach Stem Height Dependence On Msupporting

confidence: 93%

“…Here, the shock generators remain fixed, while the free-stream Mach number varies. To our knowledge, there is only one reported experimental work using a similar approach [19]. Schlieren visualization was used as the main flow diagnostics tool, and a focusing schlieren system was additionally employed to investigate three-dimensional sidewall effects.…”

Section: Introductionmentioning

confidence: 99%

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Experimental investigation of shock–shock interactions with variable inflow Mach number

et al. 2021

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Experiments on shock–shock interactions were conducted in a transonic–supersonic wind tunnel with variable free-stream Mach number functionality. Transition between the regular interaction (RI) and the Mach interaction (MI) was induced by variation of the free-steam Mach number for a fixed interaction geometry, as opposed to most previous studies where the shock generator angles are varied at constant Mach number. In this paper, we present a systematic flow-based post-processing methodology of schlieren data that enables an accurate tracking of the evolving shock system including the precise and reproducible detection of RI$$\rightleftarrows $$ ⇄ MI transition. In line with previous experimental studies dealing with noisy free-stream environments, transition hysteresis was not observed. However, we show that establishing accurate values of the flow deflections besides the Mach number is crucial to achieve experimental agreement with the von Neumann criterion, since measured flow deflections deviated significantly, up to $$1.2^{\circ }$$ 1 . 2 ∘ , from nominal wedge angles. We also report a study conducted with a focusing schlieren system with variable focal plane that supported the image processing by providing insights into the three-dimensional side-wall effects integrated in the schlieren images.

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Section: Mach Stem Height Dependence On Msupporting

confidence: 93%

Section: Introductionmentioning

confidence: 99%

Experimental investigation of shock–shock interactions with variable inflow Mach number

et al. 2021

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“…C'est une configuration qui contient deux dièdres (générateur de choc) de sections droits sous forme d'une tuyère convergente, de 60 mm de longueur ( l ), la distance ( h ) entre les deux bords d'attaque des générateurs a été maintenue à 70 mm. Il est noter que ces dimensions conduisent à un rapport de forme ( l / h ) = 1.16 [8], ce rapport est suffisamment important pour éviter que les effets de bord puissent affecter l'écoulement dans la partie centrale des plaques. Le générateur de choc supérieur est en mouvement de rotation par rapport à l'axe de rotation ' 1 O ', en utilisant la technique du maillage mobile, par contre le générateur de choc inferieur est fixe.…”

Section: Géométrie Et Paramètres De L'écoulementunclassified

Etude numérique des interférences des ondes de choc asymétrique: transitions (RR-MR) et phénomène hystérésis

Benderradji,

Beghidja,

Gouidmi

2023

J. Ren. Energies

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L’étude analytique et la recherche expérimentale sur la réflexion des ondes de choc asymétriques (interférences RR - MR), dans les écoulements supersoniques stationnaires a été rapporté pour la première fois par, Li et al. [1]. Le but de ce travail de recherche est d’effectuer des simulations numériques (CFD), sur les interférences des ondes de choc dans les écoulements supersoniques stationnaires et plus particulièrement à l’étude de la transition réflexion régulier (RR) vers réflexion de Mach (MR) et vice versa - phénomène hystérésis. Ce dernier procédé a été largement étudié numériquement dans le cas des réflexions symétrique au cours des ces dernières années. L’analyse des résultats obtenus a été basée sur des résultats expérimentaux de Li et al. [1], et comparés analytiquement par la théorie du triple choc (polaire de choc). L’étude théorique a permis l’identification des critères de transition, et montre clairement l’existence d’un phénomène hystérésis dans la transition (RR) - (MR) des ondes de choc asymétriques analogue à celui existant en interaction de choc symétrique.

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“…The authors have investigated the use of DSMC as a pseudo-Euler solver in the continuum limit by using a modification of Pullin’s Equilibrium Particle Simulation Method (EPSM). Durand et al 11 investigated the hysteresis effect due to shock waves interference in variable Mach number flows in a wind tunnel. The authors studied the transition between the Regular Reflection and Mach Reflection by varying freestream Mach Number.…”

Section: Introductionmentioning

confidence: 99%

Aerothermodynamic analysis and rear wake assessment of shock wave interference over blunt leading edge at Mach 6.5

Singh,

Sharma,

Padhy

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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A detailed numerical study of shock-wave interference on a cylindrical blunt leading edge in hypersonic flow is carried out to reveal the effect of shock-shock interaction on peak heating and blunt body aerodynamics. This study is unique in that it examines the effect of interactions on rear wake formation and aerodynamic forces acting on the blunt body. Six different shock wave interference patterns described by Edney are studied for a freestream Mach number of 6.5. Compressible Reynolds-averaged Navier–Stokes equations are solved using finite volume method to obtain accurate prediction of the flowfield and aerodynamic loads. Hugoniot jump conditions are imposed in the inlet boundary to realize oblique shock of desired strength to interact with the detached shock at specific location. Numerical predictions are in good agreement with reported experimental measurements. The results obtained in this study reveals that the type of shock-shock interaction pattern can significantly alter the characteristics of the rear wake. Comparisons to undisturbed flow conditions reveal that Type II to VI interactions lead to an increase in wake size, whereas Type I interaction shows a marginal reduction. These changes in wake size are attributed to modifications in the forebody boundary layer induced by the shock-shock interactions. In the case of Type I interaction, however, the transmitted wave interacting with the rear wake is found to be responsible for the marginal reduction in wake size. This study also shows that changes to the rear wake structure caused by the change in interaction type can affect aerodynamic loads. Type VI interaction recorded a maximum drag coefficient of 2.96, whereas Type IV interaction yielded a maximum lift coefficient of 0.992. These findings demonstrate the potential for dynamically adjusting the control forces of a flying body by manipulating shock interference.

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Investigation of shock waves interference and associated hysteresis effect at variable-Mach-number upstream flow

Cited by 6 publications

References 15 publications

Experimental investigation of shock–shock interactions with variable inflow Mach number

Experimental investigation of shock–shock interactions with variable inflow Mach number

Etude numérique des interférences des ondes de choc asymétrique: transitions (RR-MR) et phénomène hystérésis

Aerothermodynamic analysis and rear wake assessment of shock wave interference over blunt leading edge at Mach 6.5

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