A parametric study of Mach reflection in steady flows

Li, H.; Ben‐Dor, G.

doi:10.1017/s0022112097005375

Cited by 86 publications

(125 citation statements)

References 0 publications

Supporting

Mentioning

114

Contrasting

Order By: Relevance

“…The inviscid flow conditions that result in either an RR or an MR as well as the transition between the two have been widely studied (Henderson 1967;Hornung, Oertel & Sandeman 1979;Hornung & Robinson 1982;Chpoun et al 1995;Vuillon, Zeitoun & Ben-Dor 1995;Li & Ben-Dor 1997;Ben-Dor 2007).…”

Section: Inviscid Transition Criteriamentioning

confidence: 99%

Confinement effects on regular–irregular transition in shock-wave–boundary-layer interactions

Grossman

Bruce

2018

J. Fluid Mech.

View full text Add to dashboard Cite

An oblique shock wave is generated in a Mach 2 flow at a flow deflection angle of 12• . The resulting shock-wave-boundary-layer interaction (SWBLI) at the tunnel wall is observed. A novel traversable shock generator allows the position of the SWBLI to be varied relative to a downstream expansion fan. The relationship between the SWBLI, the expansion fan and the wind tunnel arrangement is studied. Schlieren photography, surface oil flow visualisation, particle image velocimetry and high-spatial-resolution wall pressure measurements are used to investigate the flow. It is observed that stream-normal movement of the shock generator downwards (towards the floor and hence the point of shock reflection) is accompanied by (1) growth in the streamwise extent of the shock-induced boundary layer separation, (2) upstream movement of the shock-induced separation point while the reattachment point remains nearly fixed, (3) an increase in separation shock strength and (4) transition between regular and irregular (Mach) reflection without an increase in incident shock strength. The role of free interaction theory in defining the separation shock angle is considered and shown to be consistent with the present measurements over a short streamwise extent. An SWBLI representation is proposed and reasoned which explains the apparent increase in separation shock strength that occurs without an increase in incident shock strength.

show abstract

Section: Inviscid Transition Criteriamentioning

confidence: 99%

Confinement effects on regular–irregular transition in shock-wave–boundary-layer interactions

Grossman

Bruce

2018

J. Fluid Mech.

View full text Add to dashboard Cite

show abstract

“…In an inviscid framework, it can be shown that m + decreases as g + increases, see e.g. Li & Ben-Dor (1997), provided that all other variables are held constant. Since the flow topology must fit well within the computational domain, g + was set to 5/4, which results in a relatively small Mach stem.…”

Section: Test Case Definitionmentioning

confidence: 99%

On the transition between regular and irregular shock patterns of shock-wave/boundary-layer interactions

Matheis

Hickel

2015

J. Fluid Mech.

View full text Add to dashboard Cite

The reflection of strong oblique shock waves at turbulent boundary layers is studied numerically and analytically. A particular emphasis is put on the transition between regular shock-wave/boundary-layer interaction (SWBLI) and Mach reflection (irregular SWBLI). The classical two-and three-shock theory and a generalised form of the free interaction theory are used for the analysis of well-resolved large-eddy simulations (LES) and for the derivation of stability criteria. We found that at a critical deflection angle across the incident shock wave, the perturbations related to the turbulent boundary layer cause bi-directional transition processes between regular and irregular shock patterns for a free-stream Mach number of Ma 0 = 2. Computational results show that the mean deflection angle across the separation shock is decoupled from the incident shock wave and can be accurately modelled by the generalised free interaction theory. On the basis of these observations, and the von Neumann and detachment criteria for the asymmetric intersection of shock waves, we derive the critical incident shock deflection angles at which the shock pattern may/must become irregular. Numerical data for a free-stream Mach number of Ma 0 = 3 confirm the existence of the dual-solution domain predicted by theory.

show abstract

“…Finally, the MS height is defined by the relation between the inlet and throat cross sectional areas of the nozzle. RTO-TR-AVT-007-V3 The phenomenon of regular and irregular shock reflections has been the subject of numerous investigations [19][20][21][22][23][24]. For a given Mach number and ratio of specific heats, only regular Reflections (RR) are possible for shock angles where the pressure rise across the primary and secondary oblique shocks is less than the pressure rise across a single normal shock at the freestream Mach number.…”

Section: Oblique Crossing Shock Interactionmentioning

confidence: 99%