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  • 1
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    Requirements for CFD validation experiments (1987)
    In:  CASI
    Details
    Publication Date: 2006-06-13
    Description: A list of requirements for computational fluid dynamics verification is analyzed and evaluated. Requirements include: clearly defined physics and modeling, sensitivity studies, range, validation to real conditions, duplication of key experiments and computations, and combining experiments and computations. All results are presented in viewgraph format.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Research Center, NASA CFD Validation Workshop; p 716-722
    Format: text
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  • 2
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    A study of the unsteadiness of crossing shock wave turbulent boundary layer interactions (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The unsteadiness of crossing shock wave turbulent boundary layer interactions at a nominal Mach number of 3 was examined by measuring wall pressure fluctuations using multiple, high frequency response, pressure transducers. The unsteadiness in the initial part of the interaction for all the interactions is similar to that of single fin interaction as studied by Tran and Bogdonoff (1987). However, for stronger interactions, flow downstream of the inviscid shock crossing position has a significant unsteady characteristic. In this unsteady region of the interaction, mean surface pressure rises significantly over the value obtained from the inviscid shock approximation. The energy spectrum of the fluctuating pressure signal shows a significant increase in the energy level at the higher frequencies.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 90-1456
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  • 3
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    Crossing shock wave turbulent boundary layer interactions - Variable angle and shock generator length geometry effects at Mach 3 (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: By comparing the detailed wall static pressure distributions for 9 inch and 11 inch long fins generating a crossing shock configuration at M = 2.93, the high resolution results of the 9 inch fins are shown to be free of exit effects. Analysis of the static pressure profiles have delineated the limited regions where the single fin results are valid. The characteristics of the complex interaction, with varying shock wave strength, have been described. The data provide a critical test for computational fluid dynamics which, in its initial phase, has performed poorly in predicting the measured wall static pressure distributions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0636
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  • 4
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    Preliminary study of the interactions caused by crossing shock waves and a turbulent boundary layer (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The subject research, the first phase of an extended study of the interaction of crossing shock waves with a turbulent boundary layer, has revealed the complexity of the resulting flow. Detailed surface visualization and mean wall static pressure distributions show little resemblance to the inviscid flow approximation, and the exploratory high frequency measurements show that the flow downstream of the theoretical inviscid shock crossing position has a significant unsteady characteristic. Further developments of the (unsteady) high frequency measurements are required to fully characterize the unsteadiness and the requirements to include this component in flowfield modeling.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 89-0359
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  • 5
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    Crossing shock wave-turbulent boundary layer interactions (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Three-dimensional interactions between crossing shock waves generated by symmetric sharp fins and a turbulent boundary layer on a flat plate are investigated experimentally and theoretically at Mach number 2.95 and freestream unit Reynolds number 1.96 x 10 to the 7th/ft. The incoming boundary layer has a thickness of 4 mm at the location of the fin leading edges. A comparison of experimental and computational results for two sets of fin angles (11 x 11 and 9 x 9 deg) shows general agreement with regard to surface pressure measurements and surface streamline patterns. The principal feature of the streamline structure is a collision of counterrotating vortical structures emanating from near the fin leading edges and meeting at the geometric centerline of the interaction.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0649
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  • 6
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    An exploratory study of a three-dimensional shock wave turbulent boundary layer interaction in a corner (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Three-dimensional shock wave turbulent boundary layer interactions in a corner have been studied at M about 3. The first phase, detailed mean wall static pressure distributions, has shown the interaction of a two-dimensional flow on one wall with the three-dimensional flow generated by a fin. Major three-dimensional effects on both flows were observed, extending from the interaction of the initial region of the three-dimensional flow and the corner. A large part of the resulting corner flow has little resemblance to either the two-dimensional or three-dimensional interacting flows.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0525
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  • 7
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    Turbulence measurements in two shock-wave/shear-layer interactions (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Measurements of the longitudinal component of the mass-flow fluctuations have been made in an 8-deg compression corner flow and a reattaching shear layer at a Mach number of approximately 2.9 and unit Reynolds number of about 7 x 10 to the 7th per m. The data include turbulence intensities and probability density distributions. Significant turbulence amplification occurs in both interactions. A qualitative explanation in terms of direct shock effects, extra strain rates, and their relative contribution, is suggested.
    Keywords: AERODYNAMICS
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  • 8
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    Structure of the wall pressure fluctuations in a shock-induced separated turbulent flow (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of an experimental study of the unsteady nature of a shock wave/turbulent boundary layer interaction. The interaction was generated using an unswept compression ramp. The incoming freestream Mach number was 2.9 and the flow was separated at the corner. An array of flush mounted miniature high frequency pressure transducers was used to make multi-channel measurements of the fluctuating wall pressure within the interaction. From the present results, an overall picture of the instantaneous structure of the unsteady shock system (as inferred from the wall pressure signals) can be constructed. The flow ahead of the corner can be considered as composed of two regions, namely the 'intermittent' region where there is essentially a single leading shock which exhibits significant streamwise 'flapping' and spanwise 'rippling', and the separated region where the flow experiences continuous compression.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0179
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  • 9
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    Turbulence measurements in a compressible reattaching shear layer (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 05, p. 591, Accession no. A83-17917
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 889-895
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  • 10
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    Hot-wire investigation of an unseparated shock-wave/turbulent boundary-layer interaction (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Previously cited in issue 15, p. 2345, Accession no. A82-31948
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 579-585
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