Добірка наукової літератури з теми "Shock-wave and separation- region interaction"
Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями
Ознайомтеся зі списками актуальних статей, книг, дисертацій, тез та інших наукових джерел на тему "Shock-wave and separation- region interaction".
Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.
Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.
Статті в журналах з теми "Shock-wave and separation- region interaction"
Estruch, D., D. G. MacManus, D. P. Richardson, N. J. Lawson, K. P. Garry, and J. L. Stollery. "Experimental study of unsteadiness in supersonic shock-wave/turbulent boundary-layer interactions with separation." Aeronautical Journal 114, no. 1155 (May 2010): 299–308. http://dx.doi.org/10.1017/s0001924000003742.
Повний текст джерелаMosele, John-Paul, Andreas Gross, and John Slater. "Numerical Investigation of Asymmetric Mach 2.5 Turbulent Shock Wave Boundary Layer Interaction." Aerospace 10, no. 5 (April 29, 2023): 417. http://dx.doi.org/10.3390/aerospace10050417.
Повний текст джерелаHuang, Xin, and David Estruch-Samper. "Low-frequency unsteadiness of swept shock-wave/turbulent-boundary-layer interaction." Journal of Fluid Mechanics 856 (October 11, 2018): 797–821. http://dx.doi.org/10.1017/jfm.2018.735.
Повний текст джерелаMosele, John-Paul, Andreas Gross, and John Slater. "Numerical Investigation of Mach 2.5 Axisymmetric Turbulent Shock Wave Boundary Layer Interactions." Aerospace 10, no. 2 (February 9, 2023): 159. http://dx.doi.org/10.3390/aerospace10020159.
Повний текст джерелаBurton, D. M. F., and H. Babinsky. "Corner separation effects for normal shock wave/turbulent boundary layer interactions in rectangular channels." Journal of Fluid Mechanics 707 (August 2, 2012): 287–306. http://dx.doi.org/10.1017/jfm.2012.279.
Повний текст джерелаChandola, Gaurav, Xin Huang, and David Estruch-Samper. "Highly separated axisymmetric step shock-wave/turbulent-boundary-layer interaction." Journal of Fluid Mechanics 828 (September 6, 2017): 236–70. http://dx.doi.org/10.1017/jfm.2017.522.
Повний текст джерелаBich Ngoc, Hoang Thi, and Nguyen Manh Hung. "Study of separation phenomenon in transonic flows produced by interaction between shock wave and boundary layer." Vietnam Journal of Mechanics 33, no. 3 (September 8, 2011): 170–81. http://dx.doi.org/10.15625/0866-7136/33/3/210.
Повний текст джерелаShahrbabaki, A. Nazarian, M. Bazazzadeh, and R. Khoshkhoo. "Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators." International Journal of Aerospace Engineering 2021 (July 14, 2021): 1–14. http://dx.doi.org/10.1155/2021/2047162.
Повний текст джерелаGU, Wenting, Binqian ZHANG, Kun MA, Dong LI, Pengfei LYU, and Jie HAN. "Investigation on the flow mechanism of nacelle airframe interaction for podded blended wing body transport." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 40, no. 2 (April 2022): 352–59. http://dx.doi.org/10.1051/jnwpu/20224020352.
Повний текст джерелаLAURENCE, S. J., and R. DEITERDING. "Shock-wave surfing." Journal of Fluid Mechanics 676 (April 6, 2011): 396–431. http://dx.doi.org/10.1017/jfm.2011.57.
Повний текст джерелаДисертації з теми "Shock-wave and separation- region interaction"
Zare, Shahneh Abolghasern. "Investigation of a sub boundary layer vortex generator for the control of separation in boundary layer-shock wave interaction." Thesis, Queen Mary, University of London, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.485561.
Повний текст джерелаÖstlund, Jan. "Supersonic flow separation with application to rocket engine nozzles." Doctoral thesis, KTH, Mechanics, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3793.
Повний текст джерелаThe increasing demand for higher performance in rocketlaunchers promotes the development of nozzles with higherperformance, which basically is achieved by increasing theexpansion ratio. However, this may lead to flow separation andensuing instationary, asymmetric forces, so-called side-loads,which may present life-limiting constraints on both the nozzleitself and other engine components. Substantial gains can bemade in the engine performance if this problem can be overcome,and hence different methods of separation control have beensuggested. However, none has so far been implemented in fullscale, due to the uncertainties involved in modeling andpredicting the flow phenomena involved.
In the present work the causes of unsteady and unsymmetricalflow separation and resulting side-loads in rocket enginenozzles are investigated. This involves the use of acombination of analytical, numerical and experimental methods,which all are presented in the thesis. A main part of the workis based on sub-scale testing of model nozzles operated withair. Hence, aspects on how to design sub-scale models that areable to capture the relevant physics of full-scale rocketengine nozzles are highlighted. Scaling laws like thosepresented in here are indispensable for extracting side-loadcorrelations from sub-scale tests and applying them tofull-scale nozzles.
Three main types of side-load mechanisms have been observedin the test campaigns, due to: (i) intermittent and randompressure fluctuations, (ii) transition in separation patternand (iii) aeroelastic coupling. All these three types aredescribed and exemplified by test results together withanalysis. A comprehensive, up-to-date review of supersonic flowseparation and side-loads in internal nozzle flows is givenwith an in-depth discussion of different approaches forpredicting the phenomena. This includes methods for predictingshock-induced separation, models for predicting side-loadlevels and aeroelastic coupling effects. Examples are presentedto illustrate the status of various methods, and theiradvantages and shortcomings are discussed.
A major part of the thesis focus on the fundamentalshock-wave turbulent boundary layer interaction (SWTBLI) and aphysical description of the phenomenon is given. Thisdescription is based on theoretical concepts, computationalresults and experimental observation, where, however, emphasisis placed on the rocket-engineering perspective. This workconnects the industrial development of rocket engine nozzles tothe fundamental research of the SWTBLI phenomenon and shows howthese research results can be utilized in real applications.The thesis is concluded with remarks on active and passive flowcontrol in rocket nozzles and directions of futureresearch.
The present work was performed at VAC's Space PropulsionDivision within the framework of European spacecooperation.
Keywords:turbulent, boundary layer, shock wave,interaction, overexpanded,rocket nozzle, flow separation,control, side-load, experiments, models, review.
Östlund, Jan. "Flow Processes in Rocket Engine Nozzles with Focus on Flow Separation and Side-Loads." Licentiate thesis, KTH, Mechanics, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-1452.
Повний текст джерелаKowalczyk, Piotr Jozef. "Validation and application of advanced soil constitutive models in numerical modelling of soil and soil-structure interaction under seismic loading." Doctoral thesis, Università degli studi di Trento, 2020. http://hdl.handle.net/11572/275675.
Повний текст джерелаKowalczyk, Piotr Jozef. "Validation and application of advanced soil constitutive models in numerical modelling of soil and soil-structure interaction under seismic loading." Doctoral thesis, Università degli studi di Trento, 2020. http://hdl.handle.net/11572/275675.
Повний текст джерелаDiop, Moussa. "Transition à la turbulence en écoulements compressibles décollés." Thesis, Aix-Marseille, 2017. http://www.theses.fr/2017AIXM0473/document.
Повний текст джерелаResearch dedicated to the study of the unsteadiness of turbulent Shock Wave Boundary Layer Interaction (SWBLI) has allowed a detailed description of this kind of interaction both experimentally and numerically. Several scenario were proposed to explain the low frequency unsteadiness observed in separated SWBLI. Nevertheless, the literature on this kind of flow involving either upstream laminar or transitional conditions is quite reduce. Within the framework of the European TFAST program, an important effort was made to develop experimental devices, in conjunction with numerical simulations, allowing a detailed study of these laminar or transitional configurations. In particular, within the framework of this thesis, a shock wave reflection configuration on a laminar boundary layer was set-up, with a nominal free stream Mach number of 1.68. Using classical metrology (Laser Doppler Anemometry, Hot WireAnemometry) that have been adapted to these particular experimental conditions, we have been able to describe the spatio-temporal properties of the interaction. The mean field has been characterized and compared with the classical theories and the results obtained in other configurations.A model describing the transition mechanisms to turbulence within the interaction has been developed. Its sensitivity to upstream conditions was studied by placing perturbations upstream of the interaction. In all cases, convective (high frequency) and stationary (low frequency) unsteadiness were observed and compared with those existing for upstream turbulent configurations. An intermediate range of convective unsteadiness (medium frequency) has been demonstrated and characterized
Kumara, Akshaya G. "Small-amplitude Oscillations in Hypersonic Double-cone Flow." Thesis, 2023. https://etd.iisc.ac.in/handle/2005/6030.
Повний текст джерелаGreene, Benton Robb. "Control of mean separation in a compression ramp shock boundary layer interaction using pulsed plasma jets." Thesis, 2014. http://hdl.handle.net/2152/25422.
Повний текст джерелаtext
Narayanaswamy, Venkateswa. "Investigation of a pulsed-plasma jet for separation shock/boundary layer interaction control." Thesis, 2010. http://hdl.handle.net/2152/ETD-UT-2010-05-1400.
Повний текст джерелаtext
Книги з теми "Shock-wave and separation- region interaction"
Hamed, A. Flow separation in shock wave boundary layer interactions at hypersonic speeds. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.
Знайти повний текст джерелаW, Barter J., and United States. National Aeronautics and Space Administration., eds. Control & reduction of unsteady pressure loads in separated shock wave turbulent boundary layer interaction: Final report on NASA grant NAG 1-1471 for the period 01/09/93 through 01/01/95. Austin, Tex: Center for Aerodynamics Research, Dept. of Aerospace Engineering & Engineering Mechanics, University of Texas at Austin, 1995.
Знайти повний текст джерелаW, Barter J., and United States. National Aeronautics and Space Administration., eds. Control & reduction of unsteady pressure loads in separated shock wave turbulent boundary layer interaction: Final report on NASA grant NAG 1-1471 for the period 01/09/93 through 01/01/95. Austin, Tex: Center for Aerodynamics Research, Dept. of Aerospace Engineering & Engineering Mechanics, University of Texas at Austin, 1995.
Знайти повний текст джерелаW, Barter J., and United States. National Aeronautics and Space Administration., eds. Control & reduction of unsteady pressure loads in separated shock wave turbulent boundary layer interaction: Final report on NASA grant NAG 1-1471 for the period 01/09/93 through 01/01/95. Austin, Tex: Center for Aerodynamics Research, Dept. of Aerospace Engineering & Engineering Mechanics, University of Texas at Austin, 1995.
Знайти повний текст джерелаD, Saunders J., and United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Знайти повний текст джерелаD, Saunders J., and United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Знайти повний текст джерелаD, Saunders J., and United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Знайти повний текст джерелаD, Saunders J., and United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Знайти повний текст джерелаSimulation of glancing shock wave and boundary layer interaction. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.
Знайти повний текст джерелаZeitlin, Vladimir. Geostrophic Adjustment and Wave–Vortex (Non)Interaction. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198804338.003.0008.
Повний текст джерелаЧастини книг з теми "Shock-wave and separation- region interaction"
Georgievskiy, P. Y., and V. A. Levin. "Front separation regions for blunt and streamlined bodies initiated by temperature wake – bow shock wave interaction." In Shock Waves, 1273–78. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85181-3_77.
Повний текст джерелаAso, Shigeru, Keiichi Karashima, Kiyoshi Sato, Satoshi Okuyama, and Shozo Maekawa. "Flow Visualization of Secondary Separation and Oscillating Shock Waves in Three-Dimensional Shock Waves-Turbulent Boundary Layer Interaction Region." In Flow Visualization VI, 607–11. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84824-7_107.
Повний текст джерелаDebiève, J. F., and P. Dupont. "Dependence Between Shock and Separation Bubble in a Shock Wave Boundary Layer Interaction." In IUTAM Symposium on Unsteady Separated Flows and their Control, 331–41. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-1-4020-9898-7_28.
Повний текст джерелаMaekawa, Syozo, Shigeru Aso, Shigehide Nakao, Kazuo Arashi, Kenji Tomioka, and Hiroyuki Yamao. "Aerodynamic Heating in Three-Dimensional Bow Shock Wave/Turbulent Boundary Layer Interaction Region." In Shock Waves @ Marseille I, 133–38. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-78829-1_21.
Повний текст джерелаHuang, X., G. Chandola, and D. Estruch-Samper. "Unsteady Separation Shock Dynamics in a Mach 4 Shock-Wave/Turbulent Boundary Layer Interaction." In 31st International Symposium on Shock Waves 1, 1007–13. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91020-8_121.
Повний текст джерелаDallmann, U., and P. Doerffer. "Three-Dimensional Flow Separation caused by Normal Shock-Wave / Turbulent Boundary-Layer Interaction." In Symposium Transsonicum III, 429–38. Berlin, Heidelberg: Springer Berlin Heidelberg, 1989. http://dx.doi.org/10.1007/978-3-642-83584-1_35.
Повний текст джерелаChandola, G., X. Huang, and D. Estruch-Samper. "Experimental Study on the Unsteadiness of an Axisymmetric Shock-Wave/Turbulent-Boundary-Layer Interaction with Separation." In 31st International Symposium on Shock Waves 1, 1067–73. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91020-8_128.
Повний текст джерелаCaballero, N. "Drag Reduction in Airfoils Using Control Devices in the Shock Wave-Boundary Layer Interaction Region." In Aerodynamic Drag Reduction Technologies, 377–84. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_40.
Повний текст джерелаDaub, Dennis, Sebastian Willems, Burkard Esser, and Ali Gülhan. "Experiments on Aerothermal Supersonic Fluid-Structure Interaction." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 323–39. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_21.
Повний текст джерелаRenane, Rachid, Rachid Allouche, Oumaima Zmit, and Bouchra Bouchama. "Aero Heating Optimization of a Hypersonic Thermochemical Non-Equilibrium Flow around Blunt Body by Application of Opposing Jet and Blunt Spike." In Hypersonic Vehicles - Applications, Recent Advances, and Perspectives [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.101659.
Повний текст джерелаТези доповідей конференцій з теми "Shock-wave and separation- region interaction"
Jian, Liu, Duan Wenhua, Zhang Liangji, and Qiao Weiyang. "Effect of Suction Side Jet on the Shock Wave Boundary Layer Interaction in Transonic Turbine." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-16256.
Повний текст джерелаShi, Ke, and Song Fu. "Study of Shock/Blade Tip Leakage Vortex/Boundary Layer Interaction in a Transonic Rotor With IDDES Method." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95252.
Повний текст джерелаSchreiber, H. A., and H. Starken. "An Investigation of a Strong Shock-Wave Turbulent Boundary Layer Interaction in a Supersonic Compressor Cascade." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-092.
Повний текст джерелаSaito, Seishiro, Masato Furukawa, Kazutoyo Yamada, Keisuke Watanabe, Akinori Matsuoka, and Naoyuki Niwa. "Mechanisms and Quantitative Evaluation of Flow Loss Generation in a Multi-Stage Transonic Axial Compressor." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90439.
Повний текст джерелаBell, Ralf M., and Leonhard Fottner. "Investigations of Shock/Boundary-Layer Interaction in a Highly Loaded Compressor Cascade." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-084.
Повний текст джерелаCzerwinska, J., P. Doerffer, and F. Magagnato. "Bifurcation of Shock Induced Separation Structures." In ASME 2001 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/imece2001/fed-24928.
Повний текст джерелаPriebe, Stephan, Daniel Wilkin, Andy Breeze-Stringfellow, Arash Mousavi, Rathakrishnan Bhaskaran, and Luke d’Aquila. "Large Eddy Simulations of a Transonic Airfoil Cascade." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-80683.
Повний текст джерелаZhongwei, He, and Zhang Shiying. "Lip Separate Flow Blowing and Analysis of Coherence of Inlet." In ASME 1985 Beijing International Gas Turbine Symposium and Exposition. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-igt-68.
Повний текст джерелаAotsuka, Mizuho, Toshinori Watanabe, and Yasuo Machina. "Role of Shock and Boundary Layer Separation on Unsteady Aerodynamic Characteristics of Oscillating Transonic Cascade." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38425.
Повний текст джерелаBiswas, Debasish, and Tomohiko Jimbo. "Studies on Characteristic Frequency and Length Scale of Shock Induced Motion in Transonic Diffuser Using a High Order LES Approach." In ASME 2015 Gas Turbine India Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gtindia2015-1225.
Повний текст джерела