A basic experimental investigation of passive control applied to a transonic interaction

Bur, Reynald; Délery, Jean; Corbel, Bernard; Soulevant, Didier; Soares, Renan Francisco

doi:10.1016/s0034-1223(98)80006-7

Cited by 10 publications

(3 citation statements)

References 5 publications

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“…[4] r Interaction in a [5] aves in a [6] Multiple (3) The side wall boundary layer separation region under the first shock is narrow e top wall, while the side wall boundary layer separation region under the first shock is very wide near the bottom wa (4) The separation region and reattachment line on the top and bottom walls of the duct with Mach 4 pseudo-shock wave were clearly shown by the liquid crystal visualization of the shear stress on the top om walls of the duct.…”

Section: Discussionmentioning

confidence: 99%

Shock wave smearing by passive control

2006

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Normal shock wave, terminating a local supersonic area on an airfoil, limits its performance and becomes a source of high speed impulsive noise. It is proposed to use passive control to disintegrate the shock wave. Details of the flow structure obtained by this method are studied numerically. A new boundary condition has been developed and the results of its application are verified against experiments in a nozzle flow. The method of shock wave disintegration has been confirmed and detailed analysis of the flow details is presented. The substitution of a shock wave by a gradual compression changes completely the source of the high speed impulsive noise and bears potential of its reduction.K eywords: transonic flows, shock wave boundary layer interaction, passive control. CLC number: O357.4 + 2 Document code: A

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Section: Discussionmentioning

confidence: 99%

Shock wave smearing by passive control

2006

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“…3 and Fig. 4 show the effect of passive control of the shock wave-boundary layer interaction [6]. A large λ-foot structure is formed which starts at the beginning of the cavity.…”

Section: Transonic Nozzle With a Flat Wallmentioning

confidence: 99%

Shock wave strength reduction by passive control using perforated plates

Doerffer

Szulc

2007

J. of Therm. Sci.

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Strong, normal shock wave, terminating a local supersonic area on an airfoil, not only limits aerodynamic performance but also becomes a source of a high-speed impulsive helicopter noise. The application of a passive control system (a cavity covered by a perforated plate) on a rotor blade should reduce the noise created by a moving shock. This article covers the numerical implementation of the Bohning/Doerffer transpiration law into the SPARC code and includes an extended validation against the experimental data for relatively simple geometries of transonic nozzles. It is a first step towards a full simulation of a helicopter rotor equipped with a noise reducing passive control device in hover and in forward flight conditions.

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“…To date, this technique has been widely used for different applications in aviation (2,3) . Different 'techniques,' both active and passive, for control of the flow characteristics through the shock interaction region have also been investigated and developed (4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14) and have had varying degrees of success. These methods involve either reducing the wave drag associated with the shock, improving the boundary-layer flow downstream of the interaction or more often than not, a combination of both.…”

Section: Experiments and Instrumentationmentioning

confidence: 99%

Influence of the height of the vortex generators in the control of shock-induced separation of the boundary layers

Cohen

Motallebi

2008

Aeronaut. j.

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u δ streamwise velocity at edge of boundary layer u τ x streamwise co-ordinate relative to shock wave location [m] y vertical distance from wall y + Δ boundary-layer thickness [mm] and is defined as a vertical distance at which the x-component of the velocity reaches 99·5% of the free-stream velocity distance of SBVG upstream of shock in terms of δ ρ air density τ w wall skin friction v air kinematic viscosity

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A basic experimental investigation of passive control applied to a transonic interaction

Cited by 10 publications

References 5 publications

Shock wave smearing by passive control

Shock wave smearing by passive control

Shock wave strength reduction by passive control using perforated plates

Influence of the height of the vortex generators in the control of shock-induced separation of the boundary layers

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