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Exploring The Structure And Dynamics Of Shock/Turbulent Boundary Layer Interactions Generated By Swept Compression Ramps In A Mach 2 Freestream, Daniel S. Allen
Exploring The Structure And Dynamics Of Shock/Turbulent Boundary Layer Interactions Generated By Swept Compression Ramps In A Mach 2 Freestream, Daniel S. Allen
Masters Theses
This thesis reports the investigation of the unsteadiness of a 2D and 3D swept shock-wave/turbulent boundary layer interaction (STBLI) and the effect the extent of subsonic flow has on the separation location. Two swept compression ramp cases are investigated at Mach 2 freestream conditions – a high sweep of 30 degrees and a low sweep of 10 degrees both having the same compression angle of 22.5 degrees in the vertical plane. Using a number of diagnostic techniques including stereoscopic and planar particle image velocimetry (PIV) and unsteady pressure sensitive paint (PSP) anchored with pressure transducers, the unsteadiness, the extent of …
An Experimental Investigation Of The Effect Of Narrowband Freestream Noise On Fundamental Transitional Shockwave-Boundary Layer Interaction Mechanisms, Zane Matthew Shoppell
An Experimental Investigation Of The Effect Of Narrowband Freestream Noise On Fundamental Transitional Shockwave-Boundary Layer Interaction Mechanisms, Zane Matthew Shoppell
Masters Theses
Recent work at the University of Tennessee Space Institute has demonstrated that the resonant behavior observed in the spectra of cylinder- and blunt-fin-generated XSBLIs is connected to fundamental fluid mechanisms within the boundary layer. Therefore, a test campaign was conducted to characterize the fundamental mechanisms that drive the low-frequency unsteadiness in cylinder- and blunt-fin-generated shockwave-boundary layer interactions, specifically shockwave-boundary layer interactions in which the incoming boundary layer is undergoing a laminar-to-turbulent transition. This research aims to develop a deeper understanding of such interactions and characterize the resonant behavior observed in past work by varying the sweepback angle of a hemicylindrical …
Upscaling And Development Of Linear Array Focused Laser Differential Interferometry For Simultaneous 1d Velocimetry And Spectral Profiling In High-Speed Flows, Kirk Davenport
Masters Theses
In this research a new configuration of linear array-focused laser differential interferometry (LA-FLDI) is described. This measurement expands on previous implementations of LA-FLDI through the use of an additional Wollaston prism. This additional prism expands the typical single LA-FLDI column into two columns of FLDI point pairs. The additional column of probed locations allows for increased spatial sampling of frequency spectra as well as the addition of simultaneous wall normal velocimetry measurements. The new configuration is used to measure the velocity profile and frequency content across a Mach 2 turbulent boundary layer at six wall normal locations simultaneously. Features of …
A Numerical Study Of The Limiting Cases Of Cylinder-Induced Shock Wave/Boundary Layer Interactions, Stefen Albert Lindorfer
A Numerical Study Of The Limiting Cases Of Cylinder-Induced Shock Wave/Boundary Layer Interactions, Stefen Albert Lindorfer
Masters Theses
One of the limiting factors in the design of supersonic and hypersonic vehicles remains the prediction and control of the high aerodynamic, thermodynamic, acoustic, and structural loads generated by a shock wave/boundary layer interaction (SWBLI or SBLI). In conjunction with an experimental campaign produced within the research group, a numerical study was performed using a semi-infinite cylinder to generate a SWBLI at Mach 1.88 with both laminar and turbulent boundary layers. The goals were not only to better understand the complex flow surrounding the cylinder-induced turbulent interaction, but also to establish the interaction bounds of the limiting cases of a …
The Design And Computational Validation Of A Mach 3 Wind Tunnel Nozzle Contour, Sarah Elizabeth Adams
The Design And Computational Validation Of A Mach 3 Wind Tunnel Nozzle Contour, Sarah Elizabeth Adams
Masters Theses
The objective of this effort was to design and validate a Mach 3 wind tunnel nozzle contour. The nozzle will be used for an existing facility, replacing a Mach 2.3 nozzle. The nozzle contour was design using the widely-distributed CONTUR code developed by Sivells. The program uses a combination of analytical solutions and the method of characteristics in order to calculate a nozzle contour. A nozzle contour adhering to the existing geometry requirements was achieved through an iterative process. The flowfield of the finalized nozzle contour was solved using ANSYS fluent. The solution results were analyzed for flow uniformity.