Show/Hide Menu
Hide/Show Apps
anonymousUser
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Videos
Videos
Thesis submission
Thesis submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Contact us
Contact us
Investigation of flowfield characteristics due to shock wave-boundary layer interaction on compression decompression corners using les
Download
index.pdf
Date
2019
Author
Karpuzcu, Irmak Taylan
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
6
views
1
downloads
Cite This
Shock wave boundary layer interactions occur in industrial flows where the flow is transonic, supersonic or hypersonic and there is an incoming boundary layer present. Many of the air crafts such as planes, rockets, missiles, re-entry vehicles, and supersonic wind tunnels experience shock wave boundary layer interactions. These interactions can take place on an air craft at several different places such as the air intakes, ramps, forebody and fins, and also the diffuser section of a supersonic wind tunnel. In this thesis study, three cases of shock wave boundary layer interactions are investigated, which are compression-expansion ramp, shock impinging on a wall and shock impinging on a compression-expansion ramp. The first case is at Mach 2.88 and with a Reynolds number of 135000 based on the incoming boundary layer thickness, while others are at Mach 2.05 and a Reynolds number of 188000 based on the incoming boundary layer thickness. OpenFOAM is used as the CFD software and solutions are performed using wall modeled large eddy simulations using wall functions. For the first two cases, the results are compared with the available experimental and numerical data. The results of the third case are novel since it has not yet been studied in the literature numerically or experimentally. The results for the first two cases were comparable to experimental results in terms of pressure distribution, flow field structures and unsteadiness whereas velocity profiles and skin friction distributions showed discrepancies especially in the separation zones.
Subject Keywords
Shock waves.
,
Shock Wave Boundary Layer Interaction (SWBLI)
,
Supersonic flows
,
Wall modeled Large Eddy Simulation (LES)
,
Wall functions
URI
http://etd.lib.metu.edu.tr/upload/12623471/index.pdf
https://hdl.handle.net/11511/43820
Collections
Graduate School of Natural and Applied Sciences, Thesis
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
I. T. Karpuzcu, “Investigation of flowfield characteristics due to shock wave-boundary layer interaction on compression decompression corners using les,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Mechanical Engineering., 2019.