CODE VALIDATION STUDY OF LAMINAR SHOCKIBOUNDARY LAYER AND SHOCK/SHOCK INTERACTIONS IN HYPERSONIC FLOW Part B: Comparison \\ith Navier-Stokes and DSMC Solutions

Harvey, J. K.; Holden, Michael; Wadhams, Timothy

doi:10.2514/6.2001-1031

Cited by 78 publications

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“…Table 1 summarizes the redefined test conditions obtained from the non-equilibrium calculations. The previously published values [5] are also shown. Note that in contrast to air flows there is substantial vibrational freezing, resulting in a lower velocity and higher density in the test section.…”

Section: Test Flow Characterisationmentioning

confidence: 56%

“…A similar process of shock interaction occurs on the bi-conic body but the process is more intense as illustrated in the composite computed density contours and Schlieren image shown in Figure 3. Full details of the results of the experimental studies have been presented at the 2001 [5] and 2002 [3] AIAA Reno meetings together with a number of computed solutions. In general, the comparisons between Navier Stokes computations and experiment have been excellent -possibly better than expected -with the size of the separated region and the magnitude of the heat transfer and pressure distributions through the separated and even in the reattachment region being in good agreement with the experimental measurements.…”

Section: Configurations Testedmentioning

confidence: 99%

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Validation of DSMC/Navier-Stokes Computations for Laminar Shock Wave/Boundary Layer Interactions in Hypersonic Flow

Harvey¹,

Holden²,

Candler³

2003

AIP Conference Proceedings

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Abstract. This paper discusses the recent progress with a validation exercise to examine the effectiveness of DSMC and NavierStokes in predicting complex flows involving shock/shock and shock/boundary layer interactions under laminar hypersonic conditions. The exercise is based on experiments conducted in the Aerothermal and Aero-Optics Evaluation Center shock tunnels using nitrogen. Under moderately rarefied conditions Navier-Stokes methods have performed very well in capturing the details of flow structure especially when non-equilibrium and slip effects are accounted for, whereas DSMC has not been as successful. In particular, the size of the separation regions is underestimated. This paper presents redefined test conditions accounting for vibrational non-equilibrium which have been substantiated by correlations obtained for pressure and heat transfer on the hollow cylinder and cone forebodies. Details are announced of two new lower density test conditions for future validation studies.

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Section: Test Flow Characterisationmentioning

confidence: 56%

Section: Configurations Testedmentioning

confidence: 99%

Validation of DSMC/Navier-Stokes Computations for Laminar Shock Wave/Boundary Layer Interactions in Hypersonic Flow

Harvey¹,

Holden²,

Candler³

2003

AIP Conference Proceedings

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“…All numerical solutions presented above and in [4] overpredict heat fluxes (by 15¥ 30%) on the forebody for most LENS cases. An additional investigation [7] of flow properties in the LENS wind tunnel revealed that the flow is vibrationally non-equilibrium under the conditions considered.…”

Section: Run 11c Casementioning

confidence: 99%

“…They were performed in LENS, an expansion shock tube situated at CALSPAN (Buffalo, US). The first set of experimental and numerical (both continuum and kinetic) studies on the flow over a hollow cylinder flare configuration was reported at the 39th AIAA Aerospace Sciences Meeting in Reno, 2001 (see, e.g., [4] and references therein). Two flare sizes were considered with the Reynolds numbers based on the cylinder part ranging between 15,000 and 30,000.…”

Section: Introductionmentioning

confidence: 99%

Statistical Simulation of Near-Continuum Flows with Separation

Markelov¹,

Ivanov²,

Gimelshein³

et al. 2003

AIP Conference Proceedings

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Abstract. Statistical simulation of flow around a hollow cylinder flare was performed for LENS Run 9 and Run 11 cases. A comparison with experimental and available numerical results shows that the kinetic approach predicts flow properties rather accurately if all the requirements inherent in the DSMC method (time step, cell size, and the total number of molecules) are satisfied. A recent study of the flow in the LENS wind tunnel shows that the flow is vibrationally non-equilibrium. A computation with corrected flow conditions for Run 11 case predicts lower heat fluxes over the forebody and the aft part of the flare which are in good agreement with experimental data.

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“…The experiments were part of a blind validation exercise, that was conducted under the auspices of the NATO Research and Technology Organization (RTO) Working Group 10 ) & Harvey et al (2001]. This exercise was part of a large coordinated effort by the working group to assess the ability of popular CFD codes to reproduce hypersonic flows that closely resemble what is encountered during actual flight.…”

Section: Low Enthalpy Double-cone Experimentsmentioning

confidence: 99%

Continuum and Particle Computations of Hypersonic Shock Interaction Flows

Chandler¹

2003

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The public reporting burden for this collectiyv.oÄ information is estimated to average 1 hour per response, including 'gathering and maintaining the data needed, arV;)Jpmpleting and reviewing the collection of information._ Send comme of information, including suggestions for reducing the burden, to Department of Defense, Washington Headqua.-(0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any otner provraim, «. ._., subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS.ces, sctior ports ..iall be REPORT DATE (DD-MM-YYYY)2. REPORT TYPE Final ReportDATES PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)Department of Aerospace Engineering and Mechanics University of Minnesota Minneapolis MN 55455 PERFORMING ORGANIZATION REPORT NUMBER SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)USAF/AFRL AFOSR 801 N. Randolph Street Arlington VA 22203 SPONSOR/MONITOR'S ACRONYM(S) AFOSR SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTDistribution Statement A. Approved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThere has been increasing interest in developing numerical methods and accurate physical models for solving computational fluid dynamics (CFD) problems of hypersonic continuum and rarefied flows. In this work, we establish a framework for validating numerical methods and physical models employed in popular CFD codes. The first main objective of this work is to assess the ability of current state-of-the-art methods to simulate challenging hypersonic flow problems by comparing to well characterized experiments. The second main objective is to provide benchmark numerical solutions to hypersonic double-cone laminar flows that can be used as code validation cases. There has been increasing interest in developing numerical methods and accurate physical models for solving computational fluid dynamics (CFD) problems of hypersonic continuum and rarefied flows. In this work, we establish a framework for validating numerical methods and physical models employed in popular CFD codes. The first main objective of this work is to assess the ability of current state-of-the-art methods to simulate challenging hypersonic flow problems by comparing to well characterized experiments. The second main objective is to provide benchmark numerical solutions to hypersonic double-cone laminar flows that can be used as code validation cases. This report has been derived from Dr. Ioannis Nompelis' Ph. D. Thesis at the University of Minnesota.We have simulated experiments of hypersonic laminar double-cone flows that were performed at the Large Energy National Shock (LENS) facility. These experiments were conducted as part of a validation effort for continuum and particle-based codes. The double-cone flow was chosen because it exhibits strong viscous/inviscid and shock interactions, ...

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CODE VALIDATION STUDY OF LAMINAR SHOCKIBOUNDARY LAYER AND SHOCK/SHOCK INTERACTIONS IN HYPERSONIC FLOW Part B: Comparison \\ith Navier-Stokes and DSMC Solutions

Cited by 78 publications

References 0 publications

Validation of DSMC/Navier-Stokes Computations for Laminar Shock Wave/Boundary Layer Interactions in Hypersonic Flow

Validation of DSMC/Navier-Stokes Computations for Laminar Shock Wave/Boundary Layer Interactions in Hypersonic Flow

Statistical Simulation of Near-Continuum Flows with Separation

Continuum and Particle Computations of Hypersonic Shock Interaction Flows

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