Mesoflaps for aeroelastic transpiration for SBLI control

Wood, Brett; Loth, Eric; Geubelle, Philippe H.

doi:10.2514/6.1999-614

Cited by 7 publications

(4 citation statements)

References 7 publications

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“…It is clear that greater deflection is required for optimal control. (23)(24)(25) However, to achieve the deflection required for optimal control, a piezoelectric material with greater strain producing capabilities than currently available is required. (26)…”

Section: Unimorph Control Limitationmentioning

confidence: 99%

Normal shock wave/turbulent boundary-layer interaction control using ‘smart’ piezoelectric actuators

et al. 2005

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This paper looks at active control of the normal shock wave/turbulent boundary layer interaction (SBLI) using smart flap actuators. The actuators are manufactured by bonding piezoelectric material to an inert substrate to control the bleed/suction rate through a plenum chamber. The cavity allows rapid thickening of the boundary-layer approaching the shock, which splits into a series of weaker shocks forming a lambda shock foot, thus reducing wave drag. Active control allows optimisation of the interaction, as it would be capable of either positioning the control region around the original shock position using a series of unimorph flaps or fixing the shock position by controlling the rate of mass transfer.The level of control achieved by unimorph piezoelectric actuators is not large because of small amounts of deflection possible. It is believed that to provide optimal control a piezoelectric material, which can provide greater strain and hence higher amounts of deflection is needed. However, currently such a piezoelectric material is not commercially available.

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Section: Unimorph Control Limitationmentioning

confidence: 99%

Normal shock wave/turbulent boundary-layer interaction control using ‘smart’ piezoelectric actuators

et al. 2005

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“…The flaps locally deflect in a cantilever mode due to the aerodynamic pressure distribution on them to achieve appropriately angled bleed and injection. Overall SMART system, under passive aeroelastic transpiration, is described in detail in (Crisman, 1999;Wood, et. al.,1999).…”

Section: Motivationmentioning

confidence: 99%

Active Supersonic Flow Control Using Hysteresis Compensation and Error Governor

Tharayil

Alleyne

2002

IFAC Proceedings Volumes

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“…In particular, the interaction between shock waves and turbulent boundary layers is a primary determinant of the performance of high-speed aircraft. Most engine inlets on military aircraft operating at speeds above Mach 2 employ active bleed, which requires ducting of bleed flow to an external surface where it is discharged (Gridley & Walker 1999;Wood et al 1999). The amount of bleed required increases significantly with Mach number and is on the order of 10-15% of the engine mass flow for Mach 3.…”

Section: Conventional Inlet Bleed Systemsmentioning

confidence: 99%

“…The viscous meshes employ an initial grid point placement from the flap surface at about a y + of unity and use a 15% geometric increase in normal-wall mesh spacing thereafter. The vertical grid resolution has been validated with turbulent skin friction distributions for subsonic and supersonic flow over a flat plate with a zero pressure-gradient condition (Wood 1999;Wood et al 1999). For an oblique shock interacting with a boundary layer exhibiting flow separation, the minimum horizontal grid spacing needed to achieve grid independence has been found to be onequarter of the upstream boundary-layer thickness, i.e., Dx50Á25d (Wood 1999).…”

Section: Shock/boundary -Layer Interactionmentioning

confidence: 99%