Optimal Control of Shock Wave Turbulent Boundary Layer Interactions Using Micro-Array Actuation

Anderson, Bernhard H.; Tinapple, J.; Surber, L.

doi:10.2514/6.2006-3197

Cited by 202 publications

(137 citation statements)

References 5 publications

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“…The geometries of the micro ramps considered in the current investigation follow the work of Anderson et al [18], and they are shown together in figure 1. The height of the micro ramp is h=4 mm, the chord length and half span angle are chosen at c=6.85h and α=24°, respectively.…”

Section: A Micro Ramp Geometry and Inflow Conditionsmentioning

confidence: 99%

Numerical and Experimental Investigations of the Supersonic Microramp Wake

Sun¹,

Scarano²,

Oudheusden³

et al. 2014

AIAA Journal

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Section: A Micro Ramp Geometry and Inflow Conditionsmentioning

confidence: 99%

Numerical and Experimental Investigations of the Supersonic Microramp Wake

Sun¹,

Scarano²,

Oudheusden³

et al. 2014

AIAA Journal

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“…The micro ramp geometry follows the configuration suggested by the work of Anderson et al [19]. Two ramps are considered with heights of h=3 and 4 mm, corresponding to 57% and 77% of the undisturbed turbulent boundary layer thickness respectively.…”

Section: B Micro-rampsmentioning

confidence: 99%

Decay of the supersonic turbulent wakes from micro-ramps

et al. 2014

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This is the accepted version of the paper.This version of the publication may differ from the final published version. The wakes resulting from micro-ramps immersed in a supersonic turbulent boundary layer at Ma=2.0 are investigated by means of particle image velocimetry (PIV). Two micro-ramps are investigated with height of 60% and 80% of the undisturbed boundary layer, respectively. The measurement domain is Permanent repository link

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“…Vortex generators submerged in the boundary layer are currently being evaluated as an alternate control method by many research groups. 4,5 Three-dimensional bumps have been investigated by Ogawa and Babinsky 6 as a means of modifying the shock structure to reduce the total pressure losses and the likelihood of separation. Gefroh et al 7 installed a plenum chamber below the SWBLI with flaps to recirculate fluid within the chamber.…”

Section: Introductionmentioning

confidence: 99%

Supersonic Inlet Flow Control Using Localized Arc Filament Plasma Actuators

Samimy¹,

Webb²,

Clifford³

2011

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Unlimited.Shock Wave/Boundary Layer Interactions (SWBLIs) occur in many applications of interest to the U.S. Air Force and could pose significant problems depending on the specific application. This study has undertaken to investigate the use of ). This frequency is similar to that at which the reflected shock oscillates in unforced SWBLIs. Therefore, LAFPAs are believed to manipulate the natural instability associated with the reflected shock oscillation. The success of the preliminary experiments motivated the design of a new, larger, more flexible facility that utilize a Variable Angle Wedge (VAW) (rather than a compression ramp) to generate the impinging shock wave for SWBLI. This facility is capable of easily generating a wide range of SWBLI strengths, but was found to be a poor environment for testing the LAFPAs control authority due to its inability to modify the LAFPA location. The necessary modifications to add this capability to the facility have been performed. This research is currently continuing with the focus on investigating the actuation authority and mechanism at various SWBLI strengths as well as on the optimization of the control authority.

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Optimal Control of Shock Wave Turbulent Boundary Layer Interactions Using Micro-Array Actuation

Cited by 202 publications

References 5 publications

Numerical and Experimental Investigations of the Supersonic Microramp Wake

Numerical and Experimental Investigations of the Supersonic Microramp Wake

Decay of the supersonic turbulent wakes from micro-ramps

Supersonic Inlet Flow Control Using Localized Arc Filament Plasma Actuators

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