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The influence of sidewall cooling on boundary layer pressure fluctuations for a two-dimensional supersonic nozzle

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Abstract

Broadband root-mean-square (rms) values and frequency spectra for pressure fluctuations in the supersonic boundary layer on a Mach 3 DeLaval nozzle sidewall and in the freestream are reported for both adiabatic and cooled surface conditions. The flat sidewall of the nozzle contained four sections independently cooled by liquid nitrogen. During the experiments, the flat sidewall was operated (1) adiabatically, (2) cooled in an approximately uniform manner to −40°C, and (3) cooled in a nonuniform manner. For all thermal boundary conditions on the sidewall, a dynamic pitot probe was traversed through the boundary layer and into the freestream to measure the broadband pressure fluctuations from 30 Hz to 100 kHz. The influence of sidewall cooling on the measured pressure fluctuations was dependent on the unit Reynolds number. Compared with the pressure fluctuations measured with an adiabatic sidewall, uniform cooling of the sidewall was found to reduce the rms pressure fluctuations in both the boundary layer and the freestream by approximately 50% at the highest stagnation pressures used (unit Reynolds numbers above 44,000/cm). Uniform cooling of the sidewall increased rms pressure fluctuations for lower stagnation pressures (unit Reynolds numbers below 44,000/cm). A reduction in the pressure fluctuation amplitude within the boundary layer resulted in a corresponding reduction in the pressure fluctuation amplitude in the test section freestream. Tests using a nonuniform temperature distribution on the sidewall indicated that cooling the portion of the sidewall covering the nozzle throat had the most influence on the pressure fluctuations in the boundary layer and in the freestream.

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References

  • Alcenius TJ, Schneider SP, Beckwith IE, White JA, Korte JJ (1996) Development of square nozzles for supersonic low-disturbance wind tunnels. J Aircr 33:1131–1138

    Google Scholar 

  • Anders JB, Stainback PC, Beckwith IE (1980) New technique for reducing test section noise in supersonic wind tunnels. AIAA J 18:5–6

    Google Scholar 

  • Beckwith IE (1975) Development of a High Reynolds number quiet wind tunnel for transition research. AIAA J 13:300–306

    Google Scholar 

  • Beckwith IE, Creel TR, Chen FJ, Kendall JM (1983) Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel. NASA TP-2180

  • Blanchard AE, Lachowicz JT, Wilkinson SP (1997) NASA Langley Mach 6 quiet wind-tunnel performance. AIAA J 35:23–28

    Google Scholar 

  • Brogan TP (1999) Effects of surface heating on stability and transition in a supersonic nozzle boundary layer. PhD Thesis, Department of Mechanical Engineering, Montana State University, Bozeman, Mont., USA

  • Chen FJ, Malik MR, Beckwith IE (1992) Goertler Instability and supersonic nozzle design. AIAA J 30:2093–2094

    Google Scholar 

  • Demetriades A (1996) Stabilization of a nozzle boundary layer by local surface heating. AIAA J 34:2490–2495

    Google Scholar 

  • Demetriades A, Mueller RL, Reda DC, King LS (1994) Boundary-layer studies in a 2-D supersonic nozzle for quiet-tunnel applications. AIAA Paper 94-2507

  • Demetriades A, George AH, Stuver R (1999) Thermal laminarization experiments on a supersonic nozzle sidewall. MSU SWT TR 99-02, Supersonic Wind Tunnel Laboratory, Department of Mechanical Engineering, Montana State University, Bozeman, Mont., USA

  • Drummond D, Rogers B, Demetriades A (1981) Design and operating characteristics of the supersonic wind tunnel. MSU SWT TR 81-01, Supersonic Wind Tunnel Laboratory, Department of Mechanical Engineering, Montana State University, Bozeman, Mont., USA

  • Harvey WD, Stainback PC, Anders JB, Cary AM (1975) Nozzle wall boundary-layer transition and freestream disturbances at Mach 5. AIAA J 13:307–314

    Google Scholar 

  • Kovasznay LSG, (1953) Turbulence in supersonic flow. J Aeronaut Sci 20:657–674

    Google Scholar 

  • Laufer J (1961) Aerodynamic noise in supersonic wind tunnels. J Aerospace Sci 28:685–692

    Google Scholar 

  • Mack LM (1975) Linear stability theory and the problem of supersonic boundary-layer transition. AIAA J 13:278–289

    Google Scholar 

  • Morkovin MV (1957) On transition experiments at moderate supersonic speeds. J Aeronaut Sci 24:480–486

    Google Scholar 

  • Morkovin MV (1959) On supersonic wind tunnels with low free-stream disturbances. J Appl Mech 26:319–324

    Google Scholar 

  • Pate SR (1971) Supersonic boundary-layer transition—effects of roughness and free-stream disturbances. AIAA J, 9:797–803

    Google Scholar 

  • Pate SR (1980) Effects of wind tunnel disturbances on boundary layer transition with emphasis on radiated noise: a review. AIAA Paper 80-0154

    Google Scholar 

  • Pate SR, Schueler CJ (1969) Radiated aerodynamic noise effects on boundary layer transition in supersonic and hypersonic wind tunnel. AIAA J 7:450–457

    Google Scholar 

  • Reed HL, Saric WS, Arnal, D (1996) Linear stability theory applied to boundary layers. Annu Rev Fluid Mech 8:389–428

    Article  Google Scholar 

  • Wolff SWD, Laub JA (1996) Low-disturbance flow measurements in the NASA Ames laminar flow supersonic wind tunnel. AIAA Paper 96-2189

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Acknowledgments

The reported work was partially supported by the State of Montana (USA) under the 1999 MONTS/EES Research Program as contract 414518. Undergraduate Research Assistant Thomas Nickou created the detailed drawings of the liquid cooled sidewall using the Pro-Engineer drawing and solids modeling program. Mr Nickou also processed many of the measured temperature distributions on the cooled sidewall to suitable graphical representations. Undergraduate Research Assistant Russell Stuver designed the system of piping and valves to supply liquid nitrogen to the cooled sidewall. Mr Stuver also performed a majority of the data processing. Technicians David Cox, Pat Vowell, and Kevin Amende skillfully machined the cooled sidewall from solid aluminum alloy plate. Dr. A. Demetriades assisted with writing the successful proposal on which the work was based, provided technical advice early in the project, and designed an improved mount for the DPP which functioned perfectly throughout the sequence of experiments.

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Correspondence to A. H. George.

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George, A.H., Amin, M.R. The influence of sidewall cooling on boundary layer pressure fluctuations for a two-dimensional supersonic nozzle. Exp Fluids 35, 58–69 (2003). https://doi.org/10.1007/s00348-003-0635-8

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  • DOI: https://doi.org/10.1007/s00348-003-0635-8

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