Stabilization of Boundary-Layer Flows Subject to Crossflow Instability with the Aid of Suction

Abegg, C.; Bippes, H.; Janke, Erik

doi:10.1007/978-3-662-03997-7_94

Cited by 7 publications

(4 citation statements)

References 3 publications

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“…Moreover, the stationary crossflow instability is sensitive to the locations of suction near the leading edge, but the Tollmien-Schlichting instability is not. Researchers [18][19][20][21] found that suction can change the initial amplitude of crossflow unstable waves compared to flow without suction. Kloker et al [22,23] proved that micron-sized suction can stabilize the crossflow waves, and they used the Upstream Flow Deformation (UFD) technique combined with suction to analyze the effects on the crossflow instability in Falkner-Skan-Cooke velocity profiles and summarized the excitation of subharmonic spanwise modes.…”

Section: Introductionmentioning

confidence: 99%

Receptivity and Stability Theory Analysis of a Transonic Swept Wing Experiment

Liu,

et al. 2023

Aerospace

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Surface suction provides an efficient way to delay boundary layer transitions. In order to verify the suction effects and determine the mechanism of suction control in transonic swept wing boundary layers, wind tunnel transition measurements in a hybrid laminar flow control (HLFC) wind tunnel model uses an infrared thermography technique in the Aircraft Research Association (ARA) 2.74 m × 2.44 m low turbulence level transonic wind tunnel. Based on the experimental data of stationary crossflow dominant transitions without and with surface suction in transonic swept wing boundary layers, in this paper, the effects on the receptivity and linear and nonlinear evolution of stationary crossflow vortices have been analyzed with the consideration of curvature. Theoretical analysis agreed with the experimental observations in regard to the transition delay caused by boundary layer suction near the leading-edge region.

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Section: Introductionmentioning

confidence: 99%

Receptivity and Stability Theory Analysis of a Transonic Swept Wing Experiment

Liu,

et al. 2023

Aerospace

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“…By applying a suction rate c q = 1.8 × 10 −3 the initial amplitude rose by a factor of about 50 compared to the unsucked flow (Arnal, Seraudie & Archambaud 2000). At DLR Göttingen (Deutsches Zentrum für Luft-und Raumfahrt) the setup of the 'Prinzipexperiment Querströmungsinstabilität' (a basic experiment on CF instability; see Bippes 1999) was modified to enable investigations on the effects of suction in three-dimensional boundary layers (Abegg, Bippes & Bertolotti 1999;Abegg, Bippes & Janke 2000). At 16 % and 35 % chords of the flat plate two suction chambers were embedded that were covered by perforated metal sheets.…”

Section: Introductionmentioning

confidence: 99%

“…Unsteady disturbances were damped by a factor of 20-30 when slits or large holes were applied, whereas no damping was noted with small holes compared to the no-suction case. As a possible explanation for this behaviour, Abegg et al (2000) stated that the strong CF vortices could lead to an enhanced growth of low-frequency secondary disturbances. Finally, they concluded that excitation of threedimensional disturbances has to be minimized by an appropriate suction distribution at the wall.…”

Section: Introductionmentioning

confidence: 99%

Investigation of suction for laminar flow control of three-dimensional boundary layers

Messing

Kloker

2010

J. Fluid Mech.

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Direct numerical simulations are employed to investigate the effects of discrete suction orifices at the wall on the disturbance evolution in laminar three-dimensional boundary-layer flows with favourable pressure gradient. Suction panels with many suction orifices can excite unstable crossflow (CF) modes even if the orifice spacing is smaller than the chordwise/spanwise wavelengths of unstable modes, caused by imperfections in the orifice order or suction strength. It has been found that the most unstable steady vortex mode leads to strong CF vortices that invoke turbulence by secondary instability even on the active suction panel. The deliberate excitation and support of stabilizing vortices that have less than two-thirds of the spanwise wavelength of the most amplified ones – known from the upstream flow deformation or micrometre-sized roughness elements technique – by the orifice order on the panel can secure the desired stabilizing effect of suction and lower the necessary suction amount significantly.

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“…Ein Ansatz zur Verzögerung der [1,2,8] und Plasmaaktuatoren [23,24,58] untersucht. Weiterhin wurde rein numerisch die Möglichkeit untersucht, direkt primäre QSI durch lokale Absaugung oder durch Plasmaaktuatoren bzgl.…”

Section: Verzögerung Der Querströmungsdominierten Transitionunclassified

Beeinflussung des laminar-turbulenten Grenzschichtumschlags durch kontrollierte Anregung stationärer Querströmungsinstabilitäten

Peter¹

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Stabilization of Boundary-Layer Flows Subject to Crossflow Instability with the Aid of Suction

Cited by 7 publications

References 3 publications

Receptivity and Stability Theory Analysis of a Transonic Swept Wing Experiment

Receptivity and Stability Theory Analysis of a Transonic Swept Wing Experiment

Investigation of suction for laminar flow control of three-dimensional boundary layers

Beeinflussung des laminar-turbulenten Grenzschichtumschlags durch kontrollierte Anregung stationärer Querströmungsinstabilitäten

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