Дисертації з теми "Hypersonic boundary-layer transition"
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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.
Повний текст джерелаRiley, Zachary Bryce Riley. "Interaction Between Aerothermally Compliant Structures and Boundary-Layer Transition in Hypersonic Flow." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1471618528.
Повний текст джерелаHusmeier, Frank. "Numerical Investigations of Transition in Hypersonic Flows over Circular Cones." Diss., The University of Arizona, 2008. http://hdl.handle.net/10150/196123.
Повний текст джерелаTirtey, Sandy C. "Characterization of a transitional hypersonic boundary layer in wind tunnel and flight conditions." Doctoral thesis, Universite Libre de Bruxelles, 2009. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210367.
Повний текст джерелаA wide bibliographic review describing the main parameters affecting transition and their coupling is proposed. The most popular roughness-induced transition predictions correlations are presented, insisting on the lack of physics included in these methods and the difficulties encountered in performing ground hypersonic transition experiments representative of real flight characteristics. This bibliographic review shows the importance of a better understanding of the physical phenomenon and of a wider experimental database, including real flight data, for the development of accurate prediction methods.
Based on the above conclusions, a hypersonic experimental test campaign is realized for the characterization of the flow field structure in the vicinity and in the wake of 3D roughness elements. This fundamental flat plate study is associated with numerical simulations for supporting the interpretation of experimental results and thus a better understanding of transition physics. Finally, a model is proposed in agreement with the wind tunnel observations and the bibliographic survey.
The second principal axis of the present study is the development of a hypersonic in-flight roughness-induced transition experiment in the frame of the European EXPERT program. These flight data, together with various wind tunnel measurements are very important for the development of a wide experimental database supporting the elaboration of future transition prediction methods.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished
Laible, Andreas Christian. "Numerical Investigation of Boundary-Layer Transition for Cones at Mach 3.5 and 6.0." Diss., The University of Arizona, 2011. http://hdl.handle.net/10150/205419.
Повний текст джерелаGrossir, Guillaume. "Longshot hypersonic wind tunnel flow characterization and boundary layer stability investigations." Doctoral thesis, Universite Libre de Bruxelles, 2015. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/209044.
Повний текст джерелаEmphasis is initially placed on the flow characterization of the Longshot wind tunnel where these experiments are performed. Free-stream static pressure diagnostics are implemented in order to complete existing stagnation point pressure and heat flux measurements on a hemispherical probe. An alternative method used to determine accurate free-stream flow conditions is then derived following a rigorous theoretical approach coupled to the VKI Mutation thermo-chemical library. Resulting sensitivities of free-stream quantities to the experimental inputs are determined and the corresponding uncertainties are quantified and discussed. The benefits of this different approach are underlined, revealing the severe weaknesses of traditional methods based on the measurement of reservoir conditions and the following assumptions of an isentropic and adiabatic flow through the nozzle. The operational map of the Longshot wind tunnel is redefined accordingly. The practical limits associated with the onset of nitrogen flow condensation under non-equilibrium conditions are also accounted for.
Boundary layer transition experiments are then performed in this environment with free-stream Mach numbers ranging between 10-12. Instrumentation along the 800mm long conical model includes flush-mounted thermocouples and fast-response pressure sensors. Transition locations on sharp cones compare favorably with engineering correlations. A strong stabilizing effect of nosetip bluntness is reported and no transition reversal regime is observed for Re_RN<120000. Wavelet analysis of wall pressure traces denote the presence of inviscid instabilities belonging to Mack's second mode. An excellent agreement with Linear Stability Theory results is obtained from which the N-factor of the Longshot wind tunnel in these conditions is inferred. A novel Schlieren technique using a short duration laser light source is developed, allowing for high-quality flow visualization of the boundary layer disturbances. Comparisons of these measurement techniques between each other are finally reported, providing a detailed view of the transition process above Mach 10.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished
Sivasubramanian, Jayahar. "Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6." Diss., The University of Arizona, 2012. http://hdl.handle.net/10150/228514.
Повний текст джерелаYentsch, Robert J. "Three-Dimensional Shock-Boundary Layer Interactions in Simulations of HIFiRE-1 and HIFiRE-2." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1384195671.
Повний текст джерелаPadilla, Montero Ivan. "Analysis of the stability of a flat-plate high-speed boundary layer with discrete roughness." Doctoral thesis, Universite Libre de Bruxelles, 2021. https://dipot.ulb.ac.be/dspace/bitstream/2013/324490/5/contratPM.pdf.
Повний текст джерелаDoctorat en Sciences de l'ingénieur et technologie
info:eu-repo/semantics/nonPublished
Di, Giovanni Antonio [Verfasser], Christian [Akademischer Betreuer] Stemmer, Wolfgang [Gutachter] Schröder, and Christian [Gutachter] Stemmer. "Roughness-Induced Transition in a Hypersonic Capsule Boundary Layer under Wind-Tunnel and Reentry Conditions / Antonio Di Giovanni ; Gutachter: Wolfgang Schröder, Christian Stemmer ; Betreuer: Christian Stemmer." München : Universitätsbibliothek der TU München, 2020. http://d-nb.info/1211725227/34.
Повний текст джерелаBura, Romie Oktovianus. "Laminar/transitional shock-wave/boundary-layer interactions (SWBLIs) in hypersonic flows." Thesis, University of Southampton, 2004. https://eprints.soton.ac.uk/47605/.
Повний текст джерелаAndré, Thierry. "Contrôle actif de la transition laminaire-turbulent en écoulement hypersonique." Thesis, Orléans, 2016. http://www.theses.fr/2016ORLE2022/document.
Повний текст джерелаDuring a hypersonic flight (Mach 6, 20 km altitude), the boundary layer developing on the forebody of a vehicle is laminar. This state may destabilize the scramjet engine propelling the vehicle. To overcome this problem during the flight, the boundary layer transition has to be forced using a control device whose effect is fixed (passive) or adjustable (active). In this work, we analyze the efficiency of a jet in crossflow in forcing the boundary layer transition on a generic forebody. The flow is computed with a Large Eddy Simulations (LES) approach. A parametric study of the injection pressure allows the efficiency of the jet in tripping the boundary layer to be quantified. The influence of flight conditions (Mach, altitude) on the transition is also studied. Dynamic Mode Decomposition (DMD) is applied to the simulation results to determine the transition leading to dynamic modes and to understand underlying transition mechanisms. Experiments in the Purdue University quiet wind tunnel (BAM6QT) were performed to quantify the efficiency of a passive transition device (diamond roughnesses) and an active transition device (single air jet) in tripping the boundary layer. A thermo-sensitive paint and pressure transducers (Kulite, PCB) were used to determine the state of the boundary layer on the generic forebody. Experimental and numerical results show a sonic injection is sufficient to induce transition. We observe from the experiments that for the same penetration height, a single roughness is less efficient than a single air jet in destabilizing the boundary layer
(8793053), Gregory R. McKiernan. "Instability and Transition on a Sliced Cone with a Finite-Span Compression Ramp at Mach 6." Thesis, 2020.
Знайти повний текст джерела(6624017), Joshua B. Edelman. "Nonlinear Growth and Breakdown of the Hypersonic Crossflow Instability." Thesis, 2019.
Знайти повний текст джерела(6196277), Elizabeth Benitez. "Instability Measurements on Two Cone-Cylinder-Flares at Mach 6." Thesis, 2021.
Знайти повний текст джерелаA cone-cylinder-flare geometry was then selected to study the instabilities related to an axisymmetric separation bubble at Mach 6. The sharp cone had a 5-degree half-angle, while flare angles of 10 degrees and 3.5 degrees were tested to compare axisymmetric compression with and without separation, respectively. Under quiet flow, laminar separation and reattachment was confirmed by schlieren and surface pressure-fluctuation measurements. Coherent traveling waves were observed. These were attributed to both the second-mode instability, as well as a shear-generated instability from the separation bubble. The symmetry of the bubble was found to be highly sensitive to angle of attack. Additionally, by introducing controlled disturbances on the cone upstream of the separation, larger-amplitude shear-generated waves were measured while the second-mode amplitudes remained unchanged. Therefore, the shear-generated waves were amplified moving through the shear layer, while the second mode remained neutrally stable. These appear to be the first measurements of traveling waves that are generated in the shear layer of a separation bubble in hypersonic flow.
(6623855), Mark Wason. "CALIBRATION OF HIGH-FREQUENCY PRESSURE SENSORS USING LOW-PRESSURE SHOCK WAVES." Thesis, 2019.
Знайти повний текст джерелаHofferth, Jerrod William. "Boundary-Layer Stability and Transition on a Flared Cone in a Mach 6 Quiet Wind Tunnel." Thesis, 2013. http://hdl.handle.net/1969.1/150990.
Повний текст джерелаRisius, Steffen. "Development of a time-resolved quantitative surface-temperature measurement technique and its application in short-duration wind tunnel testing." Thesis, 2018. http://hdl.handle.net/11858/00-1735-0000-002E-E44D-A.
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