Two-dimensional viscous simulation of inlet/diffuser flows with terminal shocks

Talcott, N. A.; Kumar, Ajay

doi:10.2514/3.22766

Cited by 9 publications

(2 citation statements)

References 3 publications

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“…For this reason, even though there are several studies of the PSW, only a few of the results are directly applicable to inlet flows. Several experimental and numerical studies of the flow in a supersonic inlet have been conducted (Talcott and Kumar 1985;Chyu et al 1989;Hamed and Shang 1991;Sajben et al 1992). However, most of those results focused on the unsteadiness of the terminal shock and did not clearly visualize the structure of PSWs inside the inlet.…”

Section: Introductionmentioning

confidence: 96%

Investigation of the pseudo-shock wave in a two-dimensional supersonic inlet

Lee

Kim

et al. 2009

J Vis

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This paper describes experimental and numerical investigations into the multiple shock waves/ turbulent boundary layer interaction in a supersonic inlet. The test model has a rectangular shape with an asymmetric subsonic diffuser of 5°. Experiments were conducted to obtain the visualization images and static pressure data by using supersonic wind tunnel. Numerical simulation was performed by solving the RANS equations with the Menter's SST turbulent model. The inflow condition was a free-stream Mach number of 2.5 and a unit Reynolds number of 7.6 9 10 7 /m. Numerical results showed good agreement with the experimental results. Based on this agreement, the flow characteristics which are often very difficult to obtain experimentally alone were analyzed with the aid of numerical simulation. The structures, pressure and velocity distributions, and total pressure loss of the pseudo-shock wave in the supersonic inlet were presented in detail from flow visualization images and static pressures.

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Section: Introductionmentioning

confidence: 96%

Investigation of the pseudo-shock wave in a two-dimensional supersonic inlet

Lee

Kim

et al. 2009

J Vis

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“…It is well known that algebraic turbulence models yield good predictions for attached turbulent flows (see, for example, Kline, Cantwell & Lilley 1981) at low to moderate subsonic speeds, where an extensive base of reliable experimental data is available to validate the computed results. Such models are often used almost without modification in prediction methods for supersonic turbulent boundary layers (see, for example, Talcott & Kumar 1985), the implicit assumption being that a compressible 'law of the wall' exists which is similar to the incompressible form (see, for example, Viegas, Rubesin & Horstman 1985;Carvin, Debieve & Smits 1988). However, the generalization of the 'law of the wall' to compressible flow has been somewhat controversial, and a number of different functional forms have been proposed (see, for example, Van Driest 1951 ; Rotta 1960;White & Christoph 1972;White 1992).…”

Section: Introductionmentioning

confidence: 99%

An asymptotic two-layer model for supersonic turbulent boundary layers

Kazakia

Walker

1995

J. Fluid Mech.

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An asymptotic analysis of the compressible turbulent boundary-layer equations is carried out for large Reynolds numbers and mainstream Mach numbers of O(1). A self-consistent two-layer asymptotic structure is described wherein the time-mean velocity and total enthalpy are logarithmic within the overlap zone but in terms of the Howarth–Dorodnitsyn variable; the proposed structure leads to a compressible law of the wall for high-speed turbulent flows with surface heat transfer. Simple outer-region algebraic turbulence models are formulated to reflect the effects of compressibility. To test the proposed asymptotic structure and turbulence models, a set of self-similar outer-region profiles for velocity and total enthalpy is obtained for constant-pressure flow and for constant wall temperature; these are combined with wall-layer profiles to form a set of composite profiles valid across the entire boundary layer. A direct comparison with experimental data shows good agreement over a wide range of conditions for flows with and without surface heat transfer.

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