An Experimental Investigation of Downstream Flow-Field Properties Behind a Sonic Jet Injected Into Transonic Free Stream from a Body of Revolution (Series II)

Dahlke, C. W.

doi:10.21236/ad0871323

Cited by 3 publications

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“…Although the work of both Romine 19 and Schilling 10 indicates that a Mach 3.73 free jet is unlikely to experience internal separation at the nominal operating conditions (case 1), neither analysis accounts for asymmetries in the backpressure. The backpressure around the exit plane of the jet will vary due to the jet-in-crossflow interaction, and this may locally induce internal separation where the backpressure is higher; i.e., in the stagnation region at the upstream edge of the jet exhaust.…”

Section: Initial Measurementsmentioning

confidence: 99%

“…[6][7][8] A few additional efforts have involved sonic jets exhausting into a subsonic compressible freestream. [9][10][11][12][13] The present research program aims to explore the flowfield behavior of a supersonic jet in subsonic compressible crossflow and to compare the results with the analogous incompressible and fully supersonic flowfields. The research presented here is restricted to the relatively simple flowfield produced by an axisymmetric jet transversely injected from a flat plate and concerns the examination of surface flow features using a fluorescent oil tracer to reveal the surface streamline patterns and extensive measurement of surface pressures.…”

Section: Introductionmentioning

confidence: 99%

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Surface Measurements of a Supersonic Jet in Subsonic Compressible Crossflow for the Validation of Computational Models

Beresh¹,

Henfling²,

Erven³

2002

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Despite many decades of jet-in-crossflow experimentation, a distinct lack of data remains for a supersonic jet exhausting into a subsonic compressible crossflow. The present investigation seeks to address this deficiency by examining the flowfield structure of a Mach 3.73 jet injected transversely from a flat plate into a subsonic compressible freestream. The experimental results described herein include the mean surface pressure field as mapped using static pressure taps on the flat plate and an identification of flow features by employing an oil-based surface flow tracer. The possibility of flow separation within the nozzle itself also is addressed using pressure taps along the nozzle interior wall, as is the asymmetry of the separation line due to the variation of the local backpressure around the perimeter of the nozzle orifice resulting from the jet-incrossflow interaction. Pressure data both on the flat plate and within the nozzle are presented at numerous angles with respect to the crossflow freestream direction to provide a breadth of measurements throughout the interaction region. Since the data are intended for use in validating computational models, attention is paid to providing details regarding the experimental geometry, boundary conditions, flowfield nonuniformities, and uncertainty analyses. Eight different sets of data are provided, covering a range of values of the jet-to-freestream dynamic pressure ratio from 2.8 to 16.9 and a freestream Mach number range of 0.5 to 0.8. 4 AcknowledgmentsThe authors would like to express their appreciation to both the Engineering Sciences Research Foundation, guided by Arthur C. Ratzel, and the Campaign 6 (formerly MAVEN) program, guided by Jaime L. Moya, for funding the research contained herein. The aforementioned program managers have exhibited great patience while substantial amounts of hardware were fabricated and rebuilt and in allowing the present study to reach fruition.In addition, the authors would like to thank the following Sandia staff members for their insightful advice and discussions, without which these efforts would have significantly less attractive results:

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Section: Initial Measurementsmentioning

confidence: 99%