Reconsideration of oblique shock wave reflections in steady flows. Part 1. Experimental investigation

1995 ◽  
Vol 301 ◽  
pp. 19-35 ◽  
Author(s):  
A. Chpoun ◽  
D. Passerel ◽  
H. Li ◽  
G. Ben-Dor
Keyword(s):  
Shock Wave ◽  
State Of The Art ◽  
Mach Reflection ◽  
Oblique Shock Wave ◽  
Steady Flows ◽  
Regular Reflection ◽  
Wave Reflections ◽  
Supersonic Wind Tunnel ◽  
Reflection Transition ◽  
Reflecting Surfaces

The reflection of shock waves over straight reflecting surfaces in steady flows was investigated experimentally using the supersonic wind tunnel of Laboratoire d'Aerothermique du CNRS, Meudon, France. The results for a flow Mach number M0 = 4.96 contradict the state of the art regarding the regular [harr ] Mach reflection transition in steady flows. Not only was a hysteresis found to exist in this transition, but, unlike previous reports, regular reflection configurations were found to be stable in the dual-solution domain in which theoretically both regular and Mach reflection are possible.

Reconsideration of oblique shock wave reflections in steady flows. Part 2. Numerical investigation

1995 ◽  
Vol 301 ◽  
pp. 37-50 ◽  
Author(s):  
J. Vuillon ◽  
D. Zeitoun ◽  
G. Ben-Dor
Keyword(s):  
Shock Wave ◽  
Shock Waves ◽  
Numerical Investigation ◽  
State Of The Art ◽  
Oblique Shock Wave ◽  
Bottom Surface ◽  
Steady Flows ◽  
Wave Reflections ◽  
The One ◽  
Reflecting Surfaces

The reflection of shock waves over straight reflecting surfaces in steady flows was investigated numerically with the aid of the LCPFCT algorithm. The findings completely supported the experimental results which were reported in Part 1 of this paper (Chpoun et al. 1995). In addition, the dependence of the resulting shock wave configuration on the distance between the trailing edge of the reflecting wedge and the bottom surface, inside the dual-solution domain, was studied. As a result of this study, as well as the one reported in Part 1, the state of the art of shock wave reflections in steady flows was reconsidered.

scholarly journals A numerical study of oblique shock-wave reflections with experimental comparisons

1985 ◽  
Vol 398 (1814) ◽  
pp. 117-140 ◽  
Keyword(s):  
Shock Wave ◽  
Numerical Study ◽  
Wedge Angle ◽  
Quantitative Agreement ◽  
Oblique Shock ◽  
Computational Method ◽  
Oblique Shock Wave ◽  
Wave Reflections ◽  
Inviscid Flows ◽  
Reflection Transition

A direct comparison is made for several occurrences of oblique shock-wave reflections between interferometric results obtained at the University of Toronto Institute for Aerospace Studies (UTIAS) 10 cm x 18 cm hyper­-velocity shock tube and numerical results obtained by using a current computational method for solving the Euler equations. Very good qualitative agreement is obtained for equilibrium and frozen flow fields except in small regions where the experiments were dominated by viscous flow. The quantitative agreement is very close in some cases but can be out by 10–15% in cases with non-equilibrium flow or viscous structures or both. Additional parametrized sequences of calculations are presented to assess the utility of the present numerical method in constructing the various reflection–transition lines for perfect inviscid flows in the shock-wave Mach number, wedge-angle ( M s , θ w )-plane, and the validity of the ‘boundary-layer defect’ theory.

Downstream flow condition effects on the RR → MR transition of asymmetric shock waves in steady flows

2009 ◽  
Vol 620 ◽  
pp. 43-62 ◽  
Author(s):  
Z. M. HU ◽  
R. S. MYONG ◽  
M. S. KIM ◽  
T. H. CHO
Keyword(s):  
Shock Waves ◽  
Mach Reflection ◽  
Flow Structures ◽  
Steady Flows ◽  
Regular Reflection ◽  
Double Wedge ◽  
Asymmetric Reflection ◽  
Asymmetric Shock ◽  
Downstream Flow ◽  
Good Agreement

In this paper, the regular reflection (RR) to Mach reflection (MR) transition of asymmetric shock waves is theoretically studied by employing the classical two- and three-shock theories. Computations are conducted to evaluate the effects of expansion fans, which are inherent flow structures in asymmetric reflection of shock waves, on the RR → MR transition. Comparison shows good agreement among the theoretical, numerical and experimental results. Some discrepancies between experiment and theory reported in previous studies are also explained based on the present theoretical analysis. The advanced RR → MR transition triggered by a transverse wave is also discussed for the interaction of a hypersonic flow and a double-wedge-like geometry.

Shock-wave reflections over double-concave cylindrical reflectors

2017 ◽  
Vol 813 ◽  
pp. 70-84 ◽  
Author(s):  
V. Soni ◽  
A. Hadjadj ◽  
A. Chaudhuri ◽  
G. Ben-Dor
Keyword(s):  
Shock Wave ◽  
Triple Point ◽  
Early Stage ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Geometrical Parameters ◽  
Regular Reflection ◽  
Wave Reflections ◽  
The Past ◽  
Shock Reflections

Numerical simulations were conducted to understand the different wave configurations associated with the shock-wave reflections over double-concave cylindrical surfaces. The reflectors were generated computationally by changing different geometrical parameters, such as the radii of curvature and the initial wedge angles. The incident-shock-wave Mach number was varied such as to cover subsonic, transonic and supersonic regimes of the flows induced by the incident shock. The study revealed a number of interesting wave features starting from the early stage of the shock interaction and transition to transitioned regular reflection (TRR) over the first concave surface, followed by complex shock reflections over the second one. Two new shock bifurcations have been found over the second wedge reflector, depending on the velocity of the additional wave that appears during the TRR over the first wedge reflector. Unlike the first reflector, the transition from a single-triple-point wave configuration (STP) to a double-triple-point wave configuration (DTP) and back occurred several times on the second reflector, indicating that the flow was capable of retaining the memory of the past events over the entire process.

The influence of the downstream pressure on the shock wave reflection phenomenon in steady flows

1999 ◽  
Vol 386 ◽  
pp. 213-232 ◽  
Author(s):  
G. BEN-DOR ◽  
T. ELPERIN ◽  
H. LI ◽  
E. VASILIEV
Keyword(s):  
Shock Wave ◽  
Wave Reflection ◽  
Numerical Study ◽  
Mach Reflection ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Steady Flows ◽  
Shock Wave Reflection ◽  
Wave Angle ◽  
Good Agreement

The effect of the downstream pressure (defined here as the wake pressure behind the tail of the reflecting wedge) on shock wave reflection in steady flows is investigated both numerically and analytically. The dependence of the shock wave configurations on the downstream pressure is studied. In addition to the incident-shock-wave-angle-induced hysteresis, which was discovered a few years ago, a new downstream- pressure-induced hysteresis has been found to exist. The numerical study reveals that when the downstream pressure is sufficiently high, an inverse-Mach reflection wave configuration, which has so far been observed only in unsteady flows, can be also established in steady flows. Very good agreement between the analytical predictions and the numerical results is found.

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