Relevant bibliographies by topics / Boundary-Layer Separation

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Boundary-Layer Separation'

Author: Grafiati
Published: 4 June 2021
Last updated: 20 April 2024

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Boundary-Layer Separation.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Boundary-Layer Separation"

1

Simpson, R. L. "Turbulent Boundary-Layer Separation." Annual Review of Fluid Mechanics 21, no. 1 (January 1989): 205–32. http://dx.doi.org/10.1146/annurev.fl.21.010189.001225.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Cao, Zhiyuan, Bo Liu, and Ting Zhang. "Control of separations in a highly loaded diffusion cascade by tailored boundary layer suction." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 228, no. 8 (October 10, 2013): 1363–74. http://dx.doi.org/10.1177/0954406213508281.

Full text
Abstract:
In order to explore the control mechanism of boundary layer suction on the separated flows of highly loaded diffusion cascades, a linear compressor cascade, which has separated flows on the whole span and three-dimensional separations over the suction surface/endwall corner, was investigated by tailored boundary layer suction. Three suction surface-slotted schemes and two combined suction surface/endwall-slotted schemes were designed. The original cascade and the cascade with part blade span suction were experimentally investigated on a high-subsonic cascade wind tunnel. In addition, numerical simulation was employed to study the flow fields of different suction schemes in detail. The results shows that while tailored boundary layer suction at part blade span can effectively remove the separations at the suction span, the flow fields of other spans deteriorated. The reasons are the ‘C’ shape or reverse ‘C’ shape spanwise distribution of static pressure after part blade span boundary layer suction. Suction surface boundary layer suction over the whole span can obviously eliminate the separation at the suction surface. However, because of the endwall boundary layer, suction surface boundary layer suction cannot effectively remove the corner three-dimensional separation. The separation over the whole span and the three-dimensional separation at the corner are completely eliminated by combined suction surface/endwall boundary layer suction. After combined boundary layer suction, the static pressure distribution over the blade span just like the shape of ‘C’ is good for the transport of the low-energy fluid near the endwall to the midspan.
APA, Harvard, Vancouver, ISO, and other styles
3

Nesteruk, Igor G. "Rigid Bodies without Boundary-Layer Separation." International Journal of Fluid Mechanics Research 41, no. 3 (2014): 260–81. http://dx.doi.org/10.1615/interjfluidmechres.v41.i3.50.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Simpson, Roger L. "Aspects of turbulent boundary-layer separation." Progress in Aerospace Sciences 32, no. 5 (October 1996): 457–521. http://dx.doi.org/10.1016/0376-0421(95)00012-7.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Smith, F. T. "Steady and Unsteady Boundary-Layer Separation." Annual Review of Fluid Mechanics 18, no. 1 (January 1986): 197–220. http://dx.doi.org/10.1146/annurev.fl.18.010186.001213.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Núñez, M. "Boundary layer separation of hydromagnetic flows." ZAMM - Journal of Applied Mathematics and Mechanics / Zeitschrift für Angewandte Mathematik und Mechanik 92, no. 6 (February 29, 2012): 445–51. http://dx.doi.org/10.1002/zamm.201100070.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Uruba, V., M. Knob, and L. Popelka. "Control of a boundary layer separation." PAMM 7, no. 1 (December 2007): 4140019–20. http://dx.doi.org/10.1002/pamm.200700945.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Peridier, Vallorie J., F. T. Smith, and J. D. A. Walker. "Vortex-induced boundary-layer separation. Part 2. Unsteady interacting boundary-layer theory." Journal of Fluid Mechanics 232, no. -1 (November 1991): 133. http://dx.doi.org/10.1017/s0022112091003658.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Ren, Xiang, Hua Su, Hua-Hua Yu, and Zheng Yan. "Wall-Modeled Large Eddy Simulation and Detached Eddy Simulation of Wall-Mounted Separated Flow via OpenFOAM." Aerospace 9, no. 12 (November 27, 2022): 759. http://dx.doi.org/10.3390/aerospace9120759.

Full text
Abstract:
Considering grid requirements of high Reynolds flow, wall-modeled large eddy simulation (WMLES) and detached eddy simulation (DES) have become the main methods to deal with near-wall turbulence. However, the flow separation phenomenon is a challenge. Three typical separated flows, including flow over a cylinder at ReD = 3900 based on the cylinder diameter, flow over a wall-mounted hump at Rec = 9.36 × 105 based on the hump length, and transonic flow over an axisymmetric bump with shock-induced separation at Rec = 2.763 × 106 based on the bump length, are used to verify WMLES, shear stress transport k-ω DES (SST-DES), and Spalart–Allmaras DES (SA-DES) methods in OpenFOAM. The three flows are increasingly challenging, namely laminar boundary layer separation, turbulent boundary layer separation, and turbulent boundary layer separation under shock interference. The results show that WMLES, SST-DES, and SA-DES methods in OpenFOAM can easily predict the separation position and wake characteristics in the flow around the cylinder, but they rely on the grid scale and turbulent inflow to accurately simulate the latter two flows. The grid requirements of Larsson et al. (δ/Δx,δ/Δy,δ/Δz≈(12,50,20)) are the basis for simulating turbulent boundary layers upstream of flow separation. A finer mesh (δ/Δx,δ/Δy,δ/Δz≈(40,75,40)) is required to accurately predict the separation and reattachment. The WMLES method is more sensitive to grid scales than the SA-DES method and fails to obtain flow separation under a coarser grid, while SST-DES method can only describe the vortices generated by the separating shear layer, but not within the turbulent boundary layer, and overestimates the separation-reattachment zone based on the grid system in this paper.
APA, Harvard, Vancouver, ISO, and other styles
10

Stieger, R. D., David Hollis, and H. P. Hodson. "Unsteady Surface Pressures Due to Wake-Induced Transition in a Laminar Separation Bubble on a Low-Pressure Cascade." Journal of Turbomachinery 126, no. 4 (October 1, 2004): 544–50. http://dx.doi.org/10.1115/1.1773851.

Full text
Abstract:
This paper presents unsteady surface pressures measured on the suction surface of a LP turbine cascade that was subject to wake passing from a moving bar wake generator. The surface pressures measured under the laminar boundary layer upstream of the steady flow separation point were found to respond to the wake passing as expected from the kinematics of wake convection. In the region where a separation bubble formed in steady flow, the arrival of the convecting wake produced high frequency, short wavelength, fluctuations in the ensemble-averaged blade surface pressure. The peak-to-peak magnitude was 30% of the exit dynamic head. The existence of fluctuations in the ensemble averaged pressure traces indicates that they are deterministic and that they are produced by coherent structures. The onset of the pressure fluctuations was found to lie beneath the convecting wake and the fluctuations were found to convect along the blade surface at half of the local freestream velocity. Measurements performed with the boundary layer tripped ahead of the separation point showed no oscillations in the ensemble average pressure traces indicating that a separating boundary layer is necessary for the generation of the pressure fluctuations. The coherent structures responsible for the large-amplitude pressure fluctuations were identified using PIV to be vortices embedded in the boundary layer. It is proposed that these vortices form in the boundary layer as the wake passes over the inflexional velocity profiles of the separating boundary layer and that the rollup of the separated shear layer occurs by an inviscid Kelvin-Helmholtz mechanism.
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Boundary-Layer Separation"

1

Lögdberg, Ola. "Turbulent Boundary Layer Separation and Control." Doctoral thesis, KTH, Linné Flow Center, FLOW, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-9821.

Full text
Abstract:
Boundary layer separation is an unwanted phenomenon in most technical applications, as for instance on airplane wings, ground vehicles and in internal flow systems. If separation occurs, it causes loss of lift, higher drag and energy losses. It is thus essential to develop methods to eliminate or delay separation.In the present experimental work streamwise vortices are introduced in turbulent boundary layers to transport higher momentum fluid towards the wall. This enables the boundary layer to stay attached at  larger pressure gradients. First the adverse pressure gradient (APG) separation bubbles that are to be eliminated are studied. It is shown that, independent of pressure gradient, the mean velocity defect profiles are self-similar when the scaling proposed by Zagarola and Smits is applied to the data. Then vortex pairs and arrays of vortices of different initial strength are studied in zero pressure gradient (ZPG). Vane-type vortex generators (VGs) are used to generate counter-rotating vortex pairs, and it is shown that the vortex core trajectories scale with the VG height h and the spanwise spacing of the blades. Also the streamwise evolution of the turbulent quantities scale with h. As the vortices are convected downstream they seem to move towards a equidistant state, where the distance from the vortex centres to the wall is half the spanwise distance between two vortices. Yawing the VGs up to 20° do not change the generated circulation of a VG pair. After the ZPG measurements, the VGs where applied in the APG mentioned above. It is shown that that the circulation needed to eliminate separation is nearly independent of the pressure gradient and that the streamwise position of the VG array relative to the separated region is not critical to the control effect. In a similar APG jet vortex generators (VGJs) are shown to as effective as the passive VGs. The ratio VR of jet velocity and test section inlet velocity is varied and a control effectiveness optimum is found for VR=5. At 40° yaw the VGJs have only lost approximately 20% of the control effect. For pulsed VGJs the pulsing frequency, the duty cycle and VR were varied. It was shown that to achieve maximum control effect the injected mass flow rate should be as large as possible, within an optimal range of jet VRs. For a given injected mass flow rate, the important parameter was shown to be the injection time t1. A non-dimensional injection time is defined as t1+ = t1Ujet/d, where d is the jet orifice diameter. Here, the optimal  t1+ was 100-200.
QC 20100825
APA, Harvard, Vancouver, ISO, and other styles
2

Lögdberg, Ola. "Turbulent boundary layer separation and control /." Stockholm : Mekanik, Kungliga Tekniska högskolan, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-9821.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Lögdberg, Ola. "Vortex generators and turbulent boundary layer separation control." Licentiate thesis, KTH, Mechanics, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4152.

Full text
Abstract:

Boundary layer separation is usually an unwanted phenomenon in most technical applications as for instance on airplane wings, on ground vehicles and in internal flows such as diffusers. If separation occurs it leads to loss of lift, higher drag and results in energy losses. It is therefore important to be able to find methods to control and if possible avoid separation altogether without introducing a too heavy penalty such as increased drag, energy consuming suction etc.

In the present work we study one such control method, namely the use of vortex generators (VGs), which are known to be able to hinder turbulent boundary layer separation. We first study the downstream development of streamwise vortices behind pairs and arrays of vortex generators and how the strength of the vortices is coupled to the relative size of the vortex generators in comparison to the boundary layer size. Both the amplitude and the trajectory of the vortices are tracked in the downstream direction. Also the influences of yaw and free stream turbulence on the vortices are investigated. This part of the study is made with hot-wire anemometry where all three velocity components of the vortex structure are measured. The generation of circulation by the VGs scales excellently with the VG blade height and the velocity at the blade edge. The magnitude of circulation was found to be independent of yaw angle.

The second part of the study deals with the control effect of vortex generators on three different cases where the strength of the adverse pressure gradient (APG) in a turbulent boundary layer has been varied. In this case the measurements have been made with particle image velocimetry. It was found that the streamwise position where the VGs are placed is not critical for the control effect. For the three different APG cases approximately the same level of circulation was needed to inhibit separation. In contrast to some previous studies we find no evidence of a universal detachment shape factor H12, that is independent of pressure gradient.

APA, Harvard, Vancouver, ISO, and other styles
4

Williams, Simon. "Three-dimensional separation of a hypersonic boundary layer." Thesis, Imperial College London, 2005. http://hdl.handle.net/10044/1/11450.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Lögdberg, Ola. "Vortex generators and turbulent boundary layer separation control /." Stockholm : Department of Mechanics, Royal Institute of Technology, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4152.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Stringer, Marc Alexander. "Separation of air flow over hills." Thesis, University of Reading, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.269964.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Angele, Kristian. "Experimental studies of turbulent boundary layer separation and control." Doctoral thesis, KTH, Mechanics, 2003. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3565.

Full text
Abstract:

The object ofthe present work is to experimentally study thecase ofa turbulent boundary layer subjected to an AdversePressure Gradient (APG) with separation and reattachment. Thisconstitutes a good test case for advanced turbulence modeling.The work consists ofde sign of a wind-tunnel setup, developmentofP article Image Velocimetry (PIV) measurements and evaluationtechniques for boundary layer flows, investigations ofs calingofb oundary layers with APG and separation and studies oftheturbulence structure ofthe separating boundary layer withcontrol by means ofs treamwise vortices. The accuracy ofP IV isinvestigated in the near-wall region ofa zero pressure-gradientturbulent boundary layer at high Reynolds number. It is shownthat, by careful design oft he experiment and correctly appliedvalidation criteria, PIV is a serious alternative toconventional techniques for well-resolved accurate turbulencemeasurements. The results from peak-locking simulationsconstitute useful guide-lines for the effect on the turbulencestatistics. Its symptoms are identified and criteria for whenthis needs to be considered are presented. Different velocityscalings are tested against the new data base on a separatingAPG boundary layer. It is shown that a velocity scale relatedto the local pressure gradient gives similarity not only forthe mean velocity but also to some extent for the Reynoldsshear-stress. Another velocity scale, which is claimed to berelated to the maximum Reynolds shear-stress, gives the samedegree of similarity which connects the two scalings. However,profile similarity achieved within an experiment is notuniversal and this flow is obviously governed by parameterswhich are still not accounted for. Turbulent boundary layerseparation control by means ofs treamwise vortices isinvestigated. The instantaneous interaction between thevortices and the boundary layer and the change in the boundarylayer and turbulence structure is presented. The vortices aregrowing with the boundary layer and the maximum vorticity isdecreased as the circulation is conserved. The vortices arenon-stationary and subjected to vortex stretching. Themovements contribute to large levels ofthe Reynolds stresses.Initially non-equidistant vortices become and remainequidistant and are con- fined to the boundary layer. Theamount ofi nitial streamwise circulationwas found to be acrucial parameter for successful separation control whereas thevortex generator position and size is ofseco ndary importance.At symmetry planes the turbulence is relaxed to a nearisotropic state and the turbulence kinetic energy is decreasedcompared to the case without vortices.

Keywords:Turbulence, Boundary layer, Separation,Adverse Pressure Gradient (APG), PIV, control, streamwisevortices, velocity scaling.

APA, Harvard, Vancouver, ISO, and other styles
8

Araki, Daisuke. "Boundary-layer separation on a moving surface in supersonic flow." Thesis, University of Manchester, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.488392.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Atcliffe, Phillip Arthur. "Effects of boundary layer separation and transition at hypersonic speeds." Thesis, Cranfield University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336458.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Cohen, Giel S. "Control of shock-induced boundary layer separation at supersonic speeds." Thesis, Queen Mary, University of London, 2007. http://qmro.qmul.ac.uk/xmlui/handle/123456789/1724.

Full text
Abstract:
The results of a systematic experimental investigation into the effects that Sub- Boundary Layer Vortex Generators (SBVGs) have on reducing normal shock-induced turbulent boundary layer separation are presented. The freestream Mach number and Reynolds number were M. = 1.45 and Re= 15-9xlO6/m, respectively. All measurement instruments and modifications to the wind tunnel were designed and manufactured as part of the project, specifically for these experiments. Boundary layer, wall pressure measurements and flow visualisation were used in the results analysis. The effects of SBVG height, lateral spacing and location upstream of the shock were investigated. A novel, curved shape SBVG was also evaluated and comparisons against the flat vane SBVG were made. The results show that in all but two cases, separation was completely eliminated. As expected, the largest SBVGs with height, h= 55%5, provided the greatest pressure recovery and maximum mixing. However, the shock pressure rise was highest for this case. Reducing the distance to shock to 108 upstream showed an improvement in the flow quality in the interaction region only. The distortion created by the vortices was also found to be closer to the wall in this case. Increasing the spacing of the SBVG pair to n-- 3 provided the greatest improvement in downstream boundary layer flow quality although this resulted in a small separated region at the foot of the shock. In order to achieve an overall improvement in flow quality, it was suggested that a compromise is required between an increase in wave drag and the extent of reduction of boundary layer separation. The effect of curving the SBVGs provided an improved near wall mixing with an improved static and surface total pressure recovery downstream of the separation region. However, an increased viscous drag resulted from these devices.
APA, Harvard, Vancouver, ISO, and other styles
More sources

Books on the topic "Boundary-Layer Separation"

1

Smith, Frank T., and Susan N. Brown, eds. Boundary-Layer Separation. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Computation of Three-Dimensional Boundary Layers Including Separation. S.l: s.n, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Computation of three-dimensional boundary layers including separation. Neuilly sur Seine, France: AGARD, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

Chang, Paul K. Recent development in flow separation. Seoul, Korea: Pang Han Pub. Co., 1985.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

United States. National Aeronautics and Space Administration., ed. Turbulent boundary layer separation over a rearward facing ramp and its control through mechanical excitation. [Washington, DC]: National Aeronautics and Space Administration, 1991.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
6

Duck, Peter W. Three-dimensional marginal separation. Hampton, Va: Institute for Computational Mechanics in Propulsion, 1988.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
7

United States. National Aeronautics and Space Administration., ed. Three-dimensional marginal separation. [Washington, D.C.]: National Aeronautics and Space Administration, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
8

United States. National Aeronautics and Space Administration., ed. Three-dimensional marginal separation. [Washington, D.C.]: National Aeronautics and Space Administration, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
9

United States. National Aeronautics and Space Administration., ed. Three-dimensional marginal separation. [Washington, D.C.]: National Aeronautics and Space Administration, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
10

Dommelen, Leon L. van. On the Lagrangian description of unsteady boundary layer separation. [Washington, D.C.]: National Aeronautics and Space Administration, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Book chapters on the topic "Boundary-Layer Separation"

1

Fornberg, Bengt. "Steady Viscous Flow Past a Cylinder and a Sphere at High Reynolds Numbers." In Boundary-Layer Separation, 3–17. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_1.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Edwards, David E. "Analysis of Three-dimensional Separated Flow Using Interacting Boundary-Layer Theory." In Boundary-Layer Separation, 163–78. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_10.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Simpson, Roger L. "A Review of Two-dimensional Turbulent Separated Flow Calculation Methods." In Boundary-Layer Separation, 179–96. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_11.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Rothmayer, A. P. "A new Interacting Boundary-Layer Formulation for Flows past Bluff Bodies." In Boundary-Layer Separation, 197–214. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_12.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Melnik, R. E. "A new Asymptotic Theory of Turbulent Boundary Layers and the Turbulent Goldstein Problem." In Boundary-Layer Separation, 217–34. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_13.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Badr, H. M., and S. C. R. Dennis. "Vortex Formation in Unsteady Flow near a Moving Wall." In Boundary-Layer Separation, 235–49. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_14.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Ghia, K. N., U. Ghia, G. A. Osswald, and C. A. Liu. "Simulation of Separated Flow Past a Bluff Body Using Navier-Stokes Equations." In Boundary-Layer Separation, 251–67. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_15.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Neiland, V. Ja. "Some Features of the Transcritical Boundary Layer Interaction and Separation." In Boundary-Layer Separation, 269–93. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_16.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Duck, P. W. "Unsteady Triple-deck Flows Leading to Instabilities." In Boundary-Layer Separation, 297–312. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_17.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Cebeci, Tuncer, Kalle Kaups, and A. A. Khattab. "Separation and Reattachment near the Leading Edge of a Thin Wing." In Boundary-Layer Separation, 313–30. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-83000-6_18.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Boundary-Layer Separation"

1

Haas, Martin, Ray-Sing Lin, and Tory Brogan. "Boundary Layer Separation Control." In 1st Flow Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2947.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Logdberg, Ola, and P. Henrik Alfredsson. "TURBULENT BOUNDARY LAYER SEPARATION - PASSIVE CONTROL." In Fourth International Symposium on Turbulence and Shear Flow Phenomena. Connecticut: Begellhouse, 2005. http://dx.doi.org/10.1615/tsfp4.920.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

SHIRAYAMA, SUSUMU, and KUNIO KUWAHARA. "Patterns of three-dimensional boundary layer separation." In 25th AIAA Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-461.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Saito, Shinya, Keisuke Udagawa, Kenji Kawaguchi, Sadatake Tomioka, and Hiroyuki Yamasaki. "Boundary Layer Separation Control by MHD Interaction." In 46th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-1091.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Cerretelli, Ciro, and Kevin Kirtley. "Boundary Layer Separation Control With Fluidic Oscillators." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90738.

Full text
Abstract:
Fluidic oscillating valves have been used in order to apply unsteady boundary layer injection to repair the separated flow of a model diffuser, where the hump pressure gradient represents that of the suction surface of a highly loaded stator vane. The fluidic actuators employed in this study consist of a fluidic oscillator that has no moving parts or temperature limitations and therefore is more attractive for implementation on production turbomachinery. The fluidic oscillators developed in this study generate an unsteady velocity with amplitudes up to 60% RMS of the average operating at non-dimensional blowing frequencies (F+) in the range 0.6 < F+ < 6. These actuators are able to fully reattach the flow and achieve maximum pressure recovery with a 60% reduction of injection momentum required and a 30% reduction in blowing power compared to optimal steady blowing. PIV velocity and vorticity measurements have been performed that show no large-scale unsteadiness in the controlled boundary layer flow.
APA, Harvard, Vancouver, ISO, and other styles
6

Klomparens, Robin, Mirko Gamba, and James F. Driscoll. "Boundary layer separation in a 3D shock train." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1519.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

McCormick, D. "Boundary layer separation control with directed synthetic jets." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-519.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Bera, Jean-Christophe, and Michel Sunyach. "Control of boundary layer separation by jet oscillation." In 4th AIAA/CEAS Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2373.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Lori, Augusto, Mahmoud Ardebili, and Yiannis Andreopoulos. "Control of Highly Loaded Airfoil Boundary Layer Separation." In ASME/JSME 2007 5th Joint Fluids Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/fedsm2007-37574.

Full text
Abstract:
Control of boundary layer separation has been investigated employing micro-actuated delta winglets. The flow with the array is simulated computationally on two-dimensional airfoil boundary layer. The simulations capture vortices formed by the impulsive motion of the delta wings. The vortices are part of recirculating zone in the wake of the actuator, which as they advect downstream, bring high momentum fluid into the near wall region of a separated flow. Preliminary results indicate micro-actuated delta wing array affect boundary layer separation favorably.
APA, Harvard, Vancouver, ISO, and other styles
10

Lori, Augusto, Mahmoud Ardebili, and Yiannis Andreopoulos. "Control of Highly Loaded Airfoil Boundary Layer Separation." In 4th Flow Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-3767.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Boundary-Layer Separation"

1

Blythe, Philip A. Theoretical Analysis of Control Mechanisms for Boundary-Layer Separation on Rotorcraft Blades. Fort Belvoir, VA: Defense Technical Information Center, June 2007. http://dx.doi.org/10.21236/ada470926.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Dolling, David S., and Noel T. Clemens. Experimental Investigation of Upstream Boundary Layer Acceleration on Unsteadiness of Shock-Induced Separation. Fort Belvoir, VA: Defense Technical Information Center, April 2003. http://dx.doi.org/10.21236/ada414559.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Smits, A. J. The Dynamic Behavior of a Turbulent Boundary Layer Subjected to a Shock-Induced Separation. Fort Belvoir, VA: Defense Technical Information Center, February 1988. http://dx.doi.org/10.21236/ada194164.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Jung, Douglas, and King Wai. Low Cost Geothermal Separators BLISS Boundary Layer Inline Separator Scrubber. Office of Scientific and Technical Information (OSTI), May 2000. http://dx.doi.org/10.2172/776847.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Bandyopadhyay, P. R. A Low-Dimensional Structural Model of a Turbulent Boundary Layer Separating Intermittently in Space. Fort Belvoir, VA: Defense Technical Information Center, September 1994. http://dx.doi.org/10.21236/ada637043.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Boundary-Layer Separation' for particular source types:
Journal articles Dissertations / Theses Books
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography