Research Papers: Flows in Complex Systems

Three-Dimensional Normal Shock-Wave/Boundary-Layer Interaction in a Diffuser

[+] Author and Article Information
Daisuke Ono

Department of Mechanical Systems Engineering,
The University of Kitakyushu,
1-1, Hibikino, Wakamatsu,
Kitakyushu City,
Fukuoka, 808-0135, Japan
e-mail: d-ono@kitakyu-u.ac.jp

Taro Handa

Associate Professor
Department of Energy and Environmental Engineering,
Kyushu University,
6-1 Kasuga-Koen,
Kasuga City,
Fukuoka, 816-8580, Japan
e-mail: t.handa@kyudai.jp

Mitsuharu Masuda

Professor Emeritus
Department of Energy and Environmental Engineering,
Kyushu University,
6-1 Kasuga-Koen,
Kasuga City,
Fukuoka, 816-8580, Japan
e-mail: michael.m.masuda@kyudai.jp

Manuscript received February 28, 2012; final manuscript received January 29, 2013; published online March 26, 2013. Assoc. Editor: Meng Wang.

J. Fluids Eng 135(4), 041105 (Mar 26, 2013) (8 pages) Paper No: FE-12-1094; doi: 10.1115/1.4023657 History: Received February 28, 2012; Revised January 29, 2013

The 3D flow structure induced by a normal shock-wave/boundary-layer interaction in a transonic diffuser is experimentally and computationally investigated. In the diffuser, the shock wave is located in the diverging section. The experiments are done with wall pressure measurements, oil-flow surface visualization, and Mach number measurements with a laser-induced fluorescence (LIF) method. In the computational work, the Reynolds-averaged Navier–Stokes equations are numerically solved with the k-ω two-equation turbulence model. The numerical solution agrees reasonably well with the experiment and clarifies the vortex structure in the interaction zone along with the 3D behavior of the boundary layer downstream of the shock wave. A careful investigation of the calculated flow reveals that the vortices are generated at the foot of the shock wave. It is also found that a complicated wave configuration is formed near the diffuser corner. A flow model is constructed by considering this wave configuration. This model explains the 3D flow characteristics in the transonic diffuser very well.

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Fig. 1

Experimental setup: 1) Ar laser, 2) mirror, 3) cylindrical lenses, 4) CCD camera, 5) personal computer, 6) balloon, 7) iodine cell, 8) stagnation chamber, 9) test diffuser, 10) expansion chamber, 11) valve, and 12) vacuum tank

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Fig. 3

Coordinate system and computational domain

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Fig. 4

Streamwise static-pressure distributions on the side wall

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Fig. 5

Oil-flow visualization (upper wall)

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Fig. 6

Schematic diagram of the oil-flow pattern on the upper wall

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Fig. 7

Limiting streamlines on the upper wall (computation)

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Fig. 8

Mach number contours on the x-z plane at y = 0 and the instantaneous schlieren image

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Fig. 9

Mach number contours on the A-A cross section

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Fig. 10

Mach number contours on the y-z plane at x = 30 mm

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Fig. 11

Velocity vectors of the secondary flow (computation)

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Fig. 12

Velocity vectors on the plane located 0.3 mm below the upper wall (computation)

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Fig. 13

Three-dimensional pathlines (computation)

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Fig. 14

Streamwise pressure gradient on the x-z plane (computation)

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Fig. 15

Streamwise pressure gradient on the A-A plane shown in Fig. 14(a) (computation)

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Fig. 16

Flow model near the upper diffuser corner

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Fig. 17

Schematic diagram of the shock wave configuration on plane C, depicted in Fig. 16



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