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TECHNICAL PAPERS

Improvement of the Performance of a Supersonic Nozzle by Riblets

[+] Author and Article Information
Kazumi Tsunoda

Department of Mechanical Engineering, Shibaura Institute of Technology, Tokyo, 108-8548, Japane-mail: ktsunoda@sic.shibaura-it.ac.jp

Tomohiko Suzuki

Namiki Precision Jewel Co., Ltd. Tokyo, 123-8511, Japan

Toshiaki Asai

Department of Mechanical Engineering, Shibaura Institute of Technology, Tokyo, 108-8548, Japan

J. Fluids Eng 122(3), 585-591 (May 02, 2000) (7 pages) doi:10.1115/1.1286991 History: Received August 24, 1999; Revised May 02, 2000
Copyright © 2000 by ASME
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References

Walsh, M. J., 1982, “Turbulent Boundary Layer Drag Reduction Using Riblets,” AIAA Paper, 82-0169.
Bacher, E. V., and Smith, C. R., 1985, “A Combined Visualization-Anemometry Study of the Turbulent Drag Reducing Mechanisms of Triangular Micro-Groove Surface Modifications,” AIAA Paper, 85-0548.
Choi,  K.-S., 1989, “Near-Wall Structure of a Turbulent Boundary Layer with Riblets,” J. Fluid Mech., 208, pp. 417–458.
Suzuki,  Y., and Kasagi,  N., 1994, “Turbulent Drag Reduction Mechanism Above a Riblet Surface,” AIAA J., 32, No. 9, pp. 1781–1790.
Chu,  D. C., and Karniadakis,  G. E., 1993, “A Direct Numerical Simulation of Laminar and Turbulent Flow over Riblet-Mounted Surfaces,” J. Fluid Mech., 250, pp. 1–42.
Choi,  H., Moin,  P., and Kim,  J., 1993, “Direct Numerical Simulation of Turbulent Flow over Riblets,” J. Fluid Mech. 255, pp. 503–539.
Squire, L. C., and Savill, A. M., 1987, “Some Experiences of Riblets at Transonic Speeds,” Proc. Intl. Conf. on Turbulent Drag Reduction by Passive Means, Royal Aero. Soc., pp. 392–407.
Gaudet,  L., 1989, “Properties of Riblets at Supersonic Speed,” Appl. Sci. Res., 46, No. 6, pp. 245–254.
Walsh, M. J., and Lindemann, A. M., 1984, “Optimization and Application of Riblets for Turbulent Drag Reduction,” AIAA Paper, 84-0347.
Winter,  K. G., and Gaudet,  L., 1973, “Turbulent Boundary-Layer Studies at High Reynolds Numbers at Mach Numbers between 0.2 and 2.8,” Aeronautical Research Council Reports and Memoranda, No. 3712.
Clauser,  F. H., 1954, “Turbulent Boundary Layers in Adverse Pressure Gradients,” J. Aeronaut. Sci., 21, pp. 91–108.

Figures

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Experimental apparatus and schematic diagram of measurement system
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Schematic cross-sectional view of the converging/diverging (CD) nozzle and coordinate system
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Cross-sectional view of the riblet surface with principal dimension
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Nondimensionalized streamwise velocity profiles in boundary layer (uncertainty in u/U0=±0.019 and in y/δ=±0.0015)
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Wall static pressure distributions along the x-direction for various operating pressure ratios
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Uncertainties of wall static pressure measurement. Error bars extend uncertainty interval at 95 percent coverage.
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Development of Mach number profile along the x-direction for Channel A and the smooth channel (uncertainty in M=±0.09 for Channel A and in M=±0.07 for the smooth channel)
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Development of Mach number profile along the x-direction for Channel B and the smooth channel (uncertainty in M=±0.08 for Channel B and in M=±0.07 for the smooth channel)
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Contour plots of stagnation pressure for the operating pressure ratio of Pb/P0S=0.1 (uncertainty in P0/P0S=±0.0066 for Channel A, in P0/P0S=±0.0097 for Channel B and in P0/P0S=±0.0068 for the smooth channel)
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Contour plots of stagnation pressure for the operating pressure ratio of Pb/P0S=0.4 (uncertainties: refer to the caption of Fig. 9)
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Streamwise variation of stagnation pressure, defined as the integral mean over the channel height, for various operating pressure ratios
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Reduction ratio in stagnation pressure loss as a function of Mach number
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Streamwise velocity profile in law of the wall coordinate (uncertainty in u+=±0.4 and in y+=±3.2)

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