Imperial College London
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DrPaulBruce

Faculty of Engineering, Department of Aeronautics

Reader in High-Speed Aerodynamics
 
 
 
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Contact

 

+44 (0)20 7594 5048p.bruce

 
 
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Location

 

333City and Guilds BuildingSouth Kensington Campus

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Summary

 

Publications

Citation

BibTex format

@article{Threadgill:2020:10.2514/1.J058918,
author = {Threadgill, J and Bruce, P},
doi = {10.2514/1.J058918},
journal = {AIAA Journal: devoted to aerospace research and development},
pages = {1--13},
title = {Unsteady flow features across different shock/boundary-layer interaction configurations},
url = {http://dx.doi.org/10.2514/1.J058918},
volume = {58},
year = {2020}
}
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RIS format (EndNote, RefMan)

TY  - JOUR
AB  - An experimental study has been conducted to investigate unsteady flow phenomena observed within various two-dimensional configurations of shock/boundary layer interactions.Six configurations have been tested in Mach 2 flow: 1 = 14 and 20compression ramps,and incident shock reflections from 1 = 7, 8, 9, and 10shock generators; Reynoldsnumbers in each case are Reθ ≈ 8350. The flow is assessed using an array of fast-responsepressure transducers in conjunction with a high-repetition rate PIV system. Developmentof the mean flow structures early in each interaction is observed to be consistent withthe Free Interaction concept. Unsteady wall-pressure energy content at frequencies abovethose associated with the characteristic low-frequency shock motion also show significantsimilarities in the vicinity of the shock foot. Results confirm that this low-frequency peakis not associated with a narrow-band forcing mechanism from either upstream or downstream, but rather a characteristic frequency that varies with interaction strength, whichdescribes the flow’s dynamic response. These findings support various models published inliterature that have sought to explain the source of low-frequency unsteady shock motion.
AU  - Threadgill,J
AU  - Bruce,P
DO  - 10.2514/1.J058918
EP  - 13
PY  - 2020///
SN  - 0001-1452
SP  - 1
TI  - Unsteady flow features across different shock/boundary-layer interaction configurations
T2  - AIAA Journal: devoted to aerospace research and development
UR  - http://dx.doi.org/10.2514/1.J058918
UR  - https://arc.aiaa.org/doi/10.2514/1.J058918
UR  - http://hdl.handle.net/10044/1/78210
VL  - 58
ER  -
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