Simulations of Normal Shock-Wave/Boundary-Layer Interaction Control Using Mesoflaps

R. K. Jaiman, E. Loth, J. C. Dutton

Research output: Contribution to journalArticlepeer-review

Abstract

Computations were performed to investigate the flowfields of normal shock-wave/boundary-layer interactions with mesoflap control. The passive control (no feedback included) concept involves placing a mesoflap streamwise array beneath the interaction and allowing high-pressure air from the flow downstream of the shock wave to recirculate through a cavity into the low-pressure flow upstream of the wave. The case of a normal shock at a Mach number of 1.4 interacting with the turbulent boundary layer on a flat wall was first considered, and the predictions yielded reasonable comparison with experimental results. A number of fixed-deflection mesoflap simulations were then performed to understand the correlations between flap deflections, downstream boundary-layer characteristics, and stagnation pressure recovery. The prescribed steady-state deflections were based on qualitative aeroelastic experimental observations. It was found that the magnitude of the deflection of the upstream mesoflaps is key to providing a significantly increased "lambda-foot" benefit, which is critical for improved stagnation pressure recovery. The number of flaps and their locations were also found to affect the stagnation pressure recovery and downstream boundary-layer characteristics significantly. However, it was found that cavity depth does not play a significant role in stagnation pressure recovery.

Original languageEnglish (US)
Pages (from-to)344-352
Number of pages9
JournalJournal of Propulsion and Power
Volume20
Issue number2
DOIs
StatePublished - 2004

ASJC Scopus subject areas

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science

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