Computations of Interaction of an Incident Oblique Shock Wave with a Turbulent Boundary Layer on a Flat Plate

Федорова, Н. Н.; Fedorchenko, I. A.

doi:10.1023/b:jamt.0000025017.49191.14

Cited by 16 publications

(11 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As noted in experiments by Dolling and Brusniak 10 and later computationally using RANS simulations by Brown, 11 Brown et al, 12 and Fedorova & Fedorchenko, 13 the associated lambda shock is unsteady, having time scales larger than, and comparable to, the turbulent boundary layer itself. This unsteadiness has also been studied computationally using higher fidelity models, such as LES.…”

Section: Introductionmentioning

confidence: 81%

Computational Analysis of Shock Wave Turbulent Boundary Layer Interaction

Leger

Poggie

2014

52nd Aerospace Sciences Meeting

View full text Add to dashboard Cite

An investigation was conducted to evaluate the error involved in predicting aerothermodynamic loads (surface pressure, skin friction, and heat transfer) using a Reynolds Averaged Navier Stokes (RANS) solver. Numerical simulations of Shock Wave / Turbulent Boundary Layer Interaction (SWTBLI) at Mach 5 are performed and compared with vetted experimental data. These simulations include three 2-D impinging shock, and two 3-D swept shock cases. The impinging shock cases involve different levels of interaction intensity, which result in attached, incipiently separated, and fully separated flows. Comparisons between the numerical results and experimental data for each case are used to evaluate the error in predicting the associated SWTBLI aero-thermodynamic loads. The result shows that while wall pressure is accurately predicted, skin friction is under predicted, and heat transfer is over predicted. However, the trends in skin friction and heat transfer are captured by the RANS simulations. Nomenclature β = Shock generator or fin deflection angle x = Streamwise distance from flat plate or fin leading edge y = Normal distance from the flat plate z = Spanwise distance from fin leading edge M = Mach number δ = Boundary layer height δ * = Boundary layer displacement thickness θ = Boundary layer momentum thickness H = Boundary layer shape factor or intersection point of separation and incident shocks γ = Angle of reattachment ε = Shock angle φ = Angle of separation ψ = Angle of upstream influence S = Line of separation R = Line of reattachment UI = Line of upstream influence P = Pressure T = Temperature M = Mach number Re/m = Unit Reynolds number U = Streamwise Velocity H o = Enthalpy ρ = Density μ = Dynamic viscosity = Dynamic viscosity from Sutherlands' law = Dynamic viscosity from Keyes' law f = Viscosity blending function ν ̃ = Eddy viscosity 1 Research Scientist, Ohio Aerospace Institute, Member AIAA. 2 Senior Aerospace Engineer, AFRL/RQHF, Associate Fellow AIAA. Downloaded by KUNGLIGA TEKNISKA HOGSKOLEN KTH on July 30, 2015 | http://arc.aiaa.org |

show abstract

Section: Introductionmentioning

confidence: 81%

Computational Analysis of Shock Wave Turbulent Boundary Layer Interaction

Leger

Poggie

2014

52nd Aerospace Sciences Meeting

View full text Add to dashboard Cite

show abstract

“…Figure 3 shows the computed results of the present work and the data of [12] on friction coefficients (Fig. 3a) and the pressure (Fig.…”

Section: Test Problemmentioning

confidence: 88%

“…The supersonic flow along a thin plate with a shock generator on the upper boundary is considered with the parameters corresponding to the experiments [12], where the freestream Mach number M 5, ∞ = the Reynolds number 6 Re 40 10 , = ⋅ the wall temperature w 300 K. T =…”

Section: Test Problemmentioning

confidence: 99%

“…In the work [11], the main attention was paid to the investigation of the structure of the shock-wave interaction with the boundary layer, the separated zone sizes and the dynamic and thermal loads realizing at a reduction or increase of the interaction intensity. The conditions were studied in the work [12], under which the shock-wave inclination angle and strength lead to the boundary layer separation.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical simulations of shock-wave interaction with a boundary layer in the plane supersonic flows with jet injection

Beketaeva

Moisseyeva

Naimanova

2016

Thermophys. Aeromech.

View full text Add to dashboard Cite

A supersonic air flow in a plane channel with a transverse turbulent jet of hydrogen injected through a slot on the bottom wall is simulated. The algorithm for solving the Favre-averaged Navier−Stokes equations for the flow of a perfect multispecies gas on the basis of the WENO scheme is proposed. The main attention is paid to the interaction of the shock-wave structure with the boundary layers on the upper and lower duct walls under the conditions of an internal turbulent flow. Namely, a detailed study of the structure of the flow is done, and separation and mixing depending on the jet slot width are investigated. It is found that in addition to well-known shock-wave structures produced by the interaction of the free stream with the transverse jet and the bow shock interaction with the boundary layers near the walls, an additional system of shock waves and the flow separation arise on the bottom wall downstream at some distance from the jet. The comparison with the experimental data is performed.

show abstract

“…In the last 20 years the investigation of the interference between shocks and boundary layers (mainly, the turbulent boundary layer) has continued [22][23][24]. Attention has again been concentrated on two-dimensional and simple three-dimensional interference.…”

mentioning

confidence: 99%

Interaction between an Inclined Shock and Boundary and High-Entropy Layers on a Flat Plate

Borovoi¹,

Егоров²,

Skuratov³

et al. 2005

Fluid Dyn

View full text Add to dashboard Cite

The flow structure and heat exchange in the zone of interference between an inclined shock and the surface of a flat plate are investigated experimentally and theoretically as functions of many parameters, the interference being studied in both the presence and the absence of bluntness of the leading edge. The experiments were carried out at Mach numbers M = 6, 8, and 10 and the Reynolds numbers Re L , calculated using the plate length L = 120 mm and the free-stream parameters, varied over the range from 0.24 · 10 6 to 1.31 · 10 6 . The bluntness radius of the leading edge of the plate, the intensity of the impinging shock, and its location with respect to the leading edge were varied. The numerical simulation was carried out by solving the complete two-dimensional Navier-Stokes equations and averaged Reynolds equations using the q-ω turbulence model. The laminar boundary layer became turbulent inside the separation zone induced by the shock. It is shown that the plate bluntness significantly reduces the heat exchange intensity in the interference zone, this effect intensifying with increase in the Mach number.

show abstract

Computations of Interaction of an Incident Oblique Shock Wave with a Turbulent Boundary Layer on a Flat Plate

Cited by 16 publications

References 14 publications

Computational Analysis of Shock Wave Turbulent Boundary Layer Interaction

Computational Analysis of Shock Wave Turbulent Boundary Layer Interaction

Numerical simulations of shock-wave interaction with a boundary layer in the plane supersonic flows with jet injection

Interaction between an Inclined Shock and Boundary and High-Entropy Layers on a Flat Plate

Contact Info

Product

Resources

About