Shock phenomena in high speed aerodynamics: still a source of major concern

Délery, Jean

doi:10.1017/s0001924000065076

Cited by 35 publications

(9 citation statements)

References 11 publications

(3 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Ashill et al suggest that this could be due to the SBVG generating compression waves that weaken the main shock wave. This observation is of interest because it ties in with shock-control methods such as passive devices [2,[9][10][11], active control [2] using blowing [2] or suction [12,13], and 2-D [14,15] or 3-D bumps [16], which work by generating compression waves that smear the shock-induced pressure rise. However, Inger and Siebersma [17] showed numerically that VGs upstream of a shock energize the boundary layer, thereby reducing the shape factor and increasing the pressure gradient and shock strength across the interaction.…”

mentioning

confidence: 99%

Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions

Holden

Babinsky

2007

Journal of Aircraft

122

View full text Add to dashboard Cite

Experiments have been performed in a blowdown supersonic wind tunnel to investigate the effect of subboundary layer vortex generators placed upstream of a normal shock/turbulent boundary layer interaction at a Mach number of 1.5 and a freestream Reynolds number of 28 10 6 . The Reynolds number based on the inflow boundary layer displacement thickness was 26,000. Two types of subboundary layer vortex generators were investigated: wedgeshaped and counter-rotating vanes. It was found that the vane-type subboundary layer vortex generators eliminated and the wedge-type subboundary layer vortex generators greatly reduced the shock-induced separation. When placed in the supersonic part of the flow, both types of subboundary layer vortex generators caused a wave pattern consisting of a shock, reexpansion, and shock. The reexpansion and double shocks are undesirable features because they equate to increased total pressure losses. Furthermore there are indications that the vortex intensity is reduced by the normal shock/boundary layer interaction. Overall, the vane-type subboundary layer vortex generators were the more effective devices as they eliminated the shock-induced separation and had the least detrimental effect on the shock structure. Nomenclaturefreestream flow velocity, ms 1 u = local flow velocity, ms 1 X = streamwise coordinate, mm Y = vertical coordinate, mm Z = spanwise coordinate, mm = boundary layer thickness, mm = boundary layer displacement thickness, mm R 0 1 u= e U e dy = boundary layer momentum thickness, mm R 0 u= e U e 1 u= e U e dy Subscripts 0 = total conditions 1 = upstream of shock 1 = freestream

show abstract

mentioning

confidence: 99%

Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions

Holden

Babinsky

2007

Journal of Aircraft

122

View full text Add to dashboard Cite

show abstract

“…One can use pressure difference across the shock to create a flow circulation (Delery 1999). This can be done by using a cavity and perforated plate in the shock wave location.…”

Section: Fig 1 Euroshock Presented Methods To Reduce Shock Wave Relmentioning

confidence: 99%

Flow Control of Transonic Airfoils using Optimum Suction and Injection Parameters

Moghadam

Jahangirian

2017

JAFM

View full text Add to dashboard Cite

In this paper, the application of the surface mass transfer optimization in shock wave-boundary layer interaction control at off-design conditions of transonic aircraft wing is presented. The suction or injection parameters include for example its position on the airfoil, its angle, the length of the hole and the rate of the injected or sucked flow. The optimization process is carried out using an efficient Genetic Algorithm (GA) method. The compressible viscous flow equations in Reynolds Averaged form are solved together with a twoequation k-epsilon turbulence model to accurately compute the objective function. Four different objective functions are introduced including maximum lift to drag ratio, minimum drag coefficient, maximum lift to drag ratio with no drag increment and minimum drag coefficient with no lift decrement. Effectiveness of each objective function is examined by comparing the optimum results in terms of the flow control parameters and flow characteristics.

show abstract

“…According to Edney's classification [20], the initial shock forms a type II shock pattern in the experiment. For detailed schematics of the six different shock patterns, refer to the work by Delery [21]. The A3 grid predicts a type I shock pattern, due to the larger separation at the foot of the shock predicted by the nonlinear turbulence model.…”

Section: Validation Casesmentioning

confidence: 99%

Parametric study of multiple shock-wave/turbulent-boundary-layer interactions with a Reynolds stress model

et al. 2021

View full text Add to dashboard Cite

The flow of high-speed air in ducts may result in the occurrence of multiple shock-wave/boundary-layer interactions. Understanding the consequences of such interactions, which may include distortion of the velocity field, enhanced turbulence production, and flow separation, is of great importance in understanding the operating limits and performance of a number of systems, for example, the high-speed intake of an air-breathing missile. In this paper, the results of a computational study of multiple shock-wave/boundary-layer interactions occurring within a high-speed intake are presented. All of the results were obtained using the in-house computational fluid dynamics solver of Glasgow University, HMB3. First simulations of a Mach $$M=1.61$$ M = 1.61 multiple shock-wave/boundary-layer interaction in a rectangular duct were performed. The $$M=1.61$$ M = 1.61 case, for which experimental data is available, was used to establish a robust numerical approach, particularly with respect to initial and boundary conditions. A number of turbulence modelling strategies were also investigated. The results suggest that Reynolds-stress-based turbulence models are better suited than linear eddy-viscosity models. This is attributed to better handling of complex strain, in particular modelling of the corner separation. The corner separations affect the separation at the centre of the domain which in turn alters the structure of the initial shock and the subsequent interaction. Having established a robust numerical approach, the results of a parametric study investigating the effect of Mach number, Reynolds number, and confinement on the baseline solution are then presented. Performance metrics are defined to help characterize the effect of the interactions. The results suggest that reduced flow confinement is beneficial for higher-pressure recovery.

show abstract

Shock phenomena in high speed aerodynamics: still a source of major concern

Cited by 35 publications

References 11 publications

Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions

Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions

Flow Control of Transonic Airfoils using Optimum Suction and Injection Parameters

Parametric study of multiple shock-wave/turbulent-boundary-layer interactions with a Reynolds stress model

Contact Info

Product

Resources

About