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Research Papers: Fundamental Issues and Canonical Flows

Effects of Surface Waviness on the Interaction of Oblique Shock Wave With Turbulent Boundary Layer

[+] Author and Article Information
Md. Saddam Hossain Joy

Department of Mechanical Engineering,
Bangladesh University of Engineering
and Technology (BUET),
Dhaka 1000, Bangladesh
e-mail: saddamhossainjoy@me.buet.ac.bd

Saeedur Rahman

Department of Mechanical Engineering,
Bangladesh University of Engineering
and Technology (BUET),
Dhaka 1000, Bangladesh
e-mail: saeed@bme.buet.ac.bd

A. B. M. Toufique Hasan

Professor
Department of Mechanical Engineering,
Bangladesh University of Engineering
and Technology (BUET),
Dhaka 1000, Bangladesh
e-mail: toufiquehasan@me.buet.ac.bd

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received April 15, 2017; final manuscript received October 11, 2017; published online December 4, 2017. Assoc. Editor: Sergio Pirozzoli.

J. Fluids Eng 140(4), 041205 (Dec 04, 2017) (12 pages) Paper No: FE-17-1230; doi: 10.1115/1.4038214 History: Received April 15, 2017; Revised October 11, 2017

Present investigation deals with the interaction of an incident oblique shock wave on a turbulent boundary layer over a wavy surface. The oblique shock wave was generated by an 8 deg wedge in a freestream Mach number of 2.0. Three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) equations with k–ω shear stress transport (SST) turbulence model were used for numerical computation. The computed results are in good agreement with the experimental measurement and direct numerical simulation (DNS) data in case of the interaction of an oblique shock with plain flat plate. To identify the effect of surface waviness on shock wave/turbulent boundary layer interaction (SWBLI), a section of the flat plate was replaced by a wavy surface. Computations have been conducted for different magnitudes of wavy amplitude. Further, the wavelength of the wavy surface has been varied. Results showed that the presence of wavy surface induces supplementary shock and expansion waves in the flow field, which are referred as topographic waves. This supplementary system of waves interacts with the counterpart of intrinsic SWBLI in a complex manner. Flow structure, separation behavior, and aerodynamic characteristics are studied. It is revealed that the amplitude is dominant than the wavelength of waviness in case of SWBLI on a wavy surface.

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Figures

Grahic Jump Location
Fig. 1

(a) Computational domain, and characteristics of wavy plate for (b) λ = 0.015 m, (c) λ = 0.010 m, computational mesh near the wavy region shown on (d) x–y plane and (e) x–z plane

Grahic Jump Location
Fig. 7

Wall pressure distribution for (a) λ = 0.015 m and (b) λ= 0.010 m

Grahic Jump Location
Fig. 2

Effect of grid size on (a) streamwise static pressure distribution, (b) skin friction coefficient as a function of nondimensional streamwise coordinate, (c) turbulent kinetic energy, and (d) its dissipation as a function of wall normal distance

Grahic Jump Location
Fig. 3

Schlieren images of SWBLI in case of flat plate (no waviness): (a) experiment [14], (b) present computation, and (c) Mach number profile before the interaction at line A

Grahic Jump Location
Fig. 4

Numerical schlieren image for SWBLI on (a) flat plate (no waviness, A = 0), and wavy plate (λ = 0.015 m), (b) A = 0.3δ0, (c) A = 0.1 δ0, and (d) A = 0.025 δ0

Grahic Jump Location
Fig. 5

Detail flow structure for SWBLI over wavy plate (λ = 0.015 m): (a) A = 0.3 δ0 and (b) A = 0.025 δ0

Grahic Jump Location
Fig. 6

Numerical schlieren image for SWBLI on wavy plate (λ=0.010 m): (a) A = 0.3 δ0, (b) A = 0.1 δ0, and (c) A = 0.025 δ0

Grahic Jump Location
Fig. 8

Velocity profile at (a) x/δ0 = 51, (b) x/δ0 = 58, (c) x/δ0 = 62, (d) x/δ0 = 67, (e) x/δ0 = 73, and (f) x/δ0 = 86

Grahic Jump Location
Fig. 9

Streamwise skin friction coefficient at the symmetry plane for (a) λ = 0.015 m and (b) λ = 0.010 m

Grahic Jump Location
Fig. 10

Height of separation bubble along streamwise direction at the symmetry plane for (a) λ = 0.015 m and (b) λ = 0.010 m

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Fig. 11

Total pressure loss along a vertical line normal to the wall at the wavy end (x/δ0 = 72)

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