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Leading edge slot blowing on an open cavity in supersonic flow

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Abstract

Supersonic flow over an open cavity can create intense pressure loads on the surfaces within the cavity. In order to combat these loads, the development of a control scheme to reduce them is becoming increasingly important for many engineering applications. The present study implements steady leading edge blowing through various configurations of spanwise-aligned rectangular leading edge slots. The effects of this control on the flow field were examined to determine the suppression mechanisms exploited by the leading edge blowing. The cavity studied here had a length-to-depth ratio of 6 and was placed in a freestream flow with a Mach number of 1.4. Actuators with one continuous slot and three and five segmented slots spanning the width of the cavity were installed at the leading edge. Surface pressure reductions of nearly 45% were achieved on the aft wall of the cavity using the 5-slot configuration. Velocity field measurements acquired through 2-component (streamwise-aligned measurement plane) and 3-component stereoscopic (cross-stream-aligned measurement plane) particle image velocimetry revealed the presence of streamwise-aligned vortices created by the segmented slots. These act to significantly alter the shear layer formed at the mouth of the cavity creating highly three-dimensional flow field features.

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Acknowledgments

The authors would like to acknowledge the support of both AFOSR through a program managed by Dr. D. Smith and the Florida Center for Advanced Aero Propulsion (FCAAP).

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Authors and Affiliations

  1. Department of Mechanical and Aerospace Engineering, University of Florida, Gainesville, FL, USA

    Taylor Lusk & Lawrence Ukeiley

  2. Department of Mechanical Engineering, FAMU-FSU College of Engineering, Tallahassee, FL, USA

    Louis Cattafesta

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  1. Taylor Lusk
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  2. Louis Cattafesta
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  3. Lawrence Ukeiley
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Correspondence to Lawrence Ukeiley.

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Lusk, T., Cattafesta, L. & Ukeiley, L. Leading edge slot blowing on an open cavity in supersonic flow. Exp Fluids 53, 187–199 (2012). https://doi.org/10.1007/s00348-012-1282-8

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  • DOI: https://doi.org/10.1007/s00348-012-1282-8

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