Experimental evidence for Plotkin model of shock unsteadiness in separated flow

Jonathan Poggie; Alexander J. Smits

doi:10.1063/1.1833405

Experimental evidence for Plotkin model of shock unsteadiness in separated flow

Jonathan Poggie, Alexander J. Smits

Mechanical & Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

36 Scopus citations

Abstract

Experimental evidence is presented in support of a model of separation shock unsteadiness developed by Plotkin [AIAA J. 13, 1036 (1975)]. Under this model, the position of the separation shock follows linearly damped Brownian motion. The model describes the manner in which relatively broad-band perturbations in the incoming flow lead to relatively low-frequency motion of the separation shock. Close agreement was found between the predictions of the model and the autospectra and autocorrelations of wall pressure fluctuations and shock position fluctuations for several blunt fin flows at Mach 3 and Mach 5. Given the similarity of the power spectra of wall-pressure fluctuations for a variety of separated, supersonic flows, this description may have broad applicability.

Original language	English (US)
Article number	018107
Pages (from-to)	018107-018107-4
Journal	Physics of Fluids
Volume	17
Issue number	1
DOIs	https://doi.org/10.1063/1.1833405
State	Published - Jan 2005

All Science Journal Classification (ASJC) codes

Computational Mechanics
Condensed Matter Physics
Mechanics of Materials
Mechanical Engineering
Fluid Flow and Transfer Processes

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title = "Experimental evidence for Plotkin model of shock unsteadiness in separated flow",

abstract = "Experimental evidence is presented in support of a model of separation shock unsteadiness developed by Plotkin [AIAA J. 13, 1036 (1975)]. Under this model, the position of the separation shock follows linearly damped Brownian motion. The model describes the manner in which relatively broad-band perturbations in the incoming flow lead to relatively low-frequency motion of the separation shock. Close agreement was found between the predictions of the model and the autospectra and autocorrelations of wall pressure fluctuations and shock position fluctuations for several blunt fin flows at Mach 3 and Mach 5. Given the similarity of the power spectra of wall-pressure fluctuations for a variety of separated, supersonic flows, this description may have broad applicability.",

author = "Jonathan Poggie and Smits, {Alexander J.}",

note = "Funding Information: This research was funded in part by grants from the Air Force Office of Scientific Research and the National Aeronautics and Space Administration Langley Research Center.",

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T1 - Experimental evidence for Plotkin model of shock unsteadiness in separated flow

AU - Poggie, Jonathan

AU - Smits, Alexander J.

N1 - Funding Information: This research was funded in part by grants from the Air Force Office of Scientific Research and the National Aeronautics and Space Administration Langley Research Center.

PY - 2005/1

Y1 - 2005/1

N2 - Experimental evidence is presented in support of a model of separation shock unsteadiness developed by Plotkin [AIAA J. 13, 1036 (1975)]. Under this model, the position of the separation shock follows linearly damped Brownian motion. The model describes the manner in which relatively broad-band perturbations in the incoming flow lead to relatively low-frequency motion of the separation shock. Close agreement was found between the predictions of the model and the autospectra and autocorrelations of wall pressure fluctuations and shock position fluctuations for several blunt fin flows at Mach 3 and Mach 5. Given the similarity of the power spectra of wall-pressure fluctuations for a variety of separated, supersonic flows, this description may have broad applicability.

AB - Experimental evidence is presented in support of a model of separation shock unsteadiness developed by Plotkin [AIAA J. 13, 1036 (1975)]. Under this model, the position of the separation shock follows linearly damped Brownian motion. The model describes the manner in which relatively broad-band perturbations in the incoming flow lead to relatively low-frequency motion of the separation shock. Close agreement was found between the predictions of the model and the autospectra and autocorrelations of wall pressure fluctuations and shock position fluctuations for several blunt fin flows at Mach 3 and Mach 5. Given the similarity of the power spectra of wall-pressure fluctuations for a variety of separated, supersonic flows, this description may have broad applicability.

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Experimental evidence for Plotkin model of shock unsteadiness in separated flow

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