Navier-Stokes solutions for mixed compression axisymmetric inlet flow with terminal shock

Chyu, W. J.; Kawamura, Tetuya; Bencze, D. P.

doi:10.2514/3.23106

Cited by 13 publications

(2 citation statements)

References 2 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: 98%

“…Many previous investigations of PSWs were conducted in constant-area channels where the effects that are associated with a sustained post-shock pressure-gradient are either totally absent or greatly suppressed (Sun et al 2003;Matsuo et al 1999;Chyu et al 1989;Hamed and Shang 1991;Waltrup and Billig 1973;Curran et al 1996;Sugiyama et al 1998). However, the phenomenon of PSWs in asymmetrically diverging diffusers of supersonic inlets is different from that in constant-area channels.…”

Section: Introductionmentioning

confidence: 98%

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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: 98%

Section: Introductionmentioning

confidence: 98%

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

Lee

Kim

et al. 2009

J Vis

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Navier‐Stokes simulation of flow through a highly contoured subsonic diffuser

Chyu¹,

Bencze²

1992

Numerical Meth Engineering

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SUMMARYThe flow through a highly offset subsonic diffuser with cross-sectional profiles that varied from rectangular at the duct entrance to circular a t the engine face was numerically simulated. A multizonal approach combined with a two-grid topology was used to represent both the internal and external flow fields, and an implicit, approximately-factored, partially flux-split finite-difference algorithm was used to solve the threedimensional thin-layer Navier-Stokes equations. The computed static pressures along the inlet wall and total pressures on the engine face were compared with experimental data. In addition, the overall flow field within the duct was examined in detail. Good agreement is shown between experiment and computations, with the limiting factor being the lack of a reliable turbulence model for internal flow problems.

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