Penetration of a Transverse Supersonic Jet into a Subsonic Compressible Crossflow

Beresh, Steven J.; Henfling, John F.; Erven, Rocky J.; Spillers, Russell Wayne

doi:10.2514/6.2004-1112

Cited by 13 publications

(33 citation statements)

References 43 publications

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“…In this region the time-averaged velocity field is dominated by a single streamwise-oriented counter-rotating vortex pair [10]. The single counter-rotating vortex pair observed in the time-averaged flow emerges from the merging of three smaller longitudinal trailing vortices [14]; two vortices are developed by contact between the slow jet fluid downstream of the Mach disk and the fast freestream, the other originates on the windward side of the barrel shock.…”

Section: Introductionmentioning

confidence: 99%

“…The shock structure consists of a bow shock (4) and re-circulation region ahead of the jet (9), a PrandtlMeyer expansion fan centred at the edge of the jet nozzle (8), barrel shocks (3) and a Mach disk (5). A single horseshoe vortex (12) is present near the plate and wraps around the base of the jet [9], while a counter-rotating vortex pair (11) dominates the far-field [10]. While the time-averaged flow-field is well documented, these structures exhibit significant temporal variations.…”

Section: Introductionmentioning

confidence: 99%

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Transient interaction between a reaction control jet and a hypersonic crossflow

et al. 2018

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This paper presents a numerical study that focuses on the transient interaction between a reaction control jet and a hypersonic crossflow with a laminar boundary layer. The aim is to better understand the underlying physical mechanisms affecting the resulting surface pressure and control force. Implicit large-eddy simulations were performed with a round, sonic, perfect air jet issuing normal to a Mach 5 crossflow over a flat plate with a laminar boundary layer, at a jet-to-crossflow momentum ratio of 5.3 and a pressure ratio of 251. The pressure distribution induced on the flat plate is unsteady and is influenced by vortex structures that form around the jet. A horseshoe vortex structure forms upstream, and consists of six vortices: two quasi-steady vortices and two co-rotating vortex pairs that periodically coalesce. Shear-layer vortices shed periodically and cause localised high pressure regions that convect downstream with constant velocity. A longitudinal counter-rotating vortex pair is present downstream of the jet, and is formed from a series of trailing vortices which rotate about a common axis. Shear-layer vortex shedding causes periodic deformation of barrel and bow shocks. This changes the location of boundary layer separation which also affects the normal force on the plate. * warrick.miller@adelaide.edu.au.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Transient interaction between a reaction control jet and a hypersonic crossflow

et al. 2018

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“…Research on plume/freestream interaction for axisymmetric nozzles [1][2][3][4][5][6][7][8] indicates that the nondimensional parameter J has been successful in correlating plume-freestream interaction phenomena such as plume penetration into the freestream. J is defined by…”

Section: Experimental Characterization Of Spin Motor Nozzle Flow Intrmentioning

confidence: 99%

Experimental characterization of spin motor nozzle flow.

Erven¹,

Peterson²,

Henfling³

2006

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The Mach number in the inviscid core of the flow exiting scarfed supersonic nozzles was measured using pitot probes. Nozzle characterization experiments were conducted in a modified section of an obsolete M = 7.3 test section/nozzle assembly on Sandia's Hypersonic Wind Tunnel. By capitalizing on existing hardware, the cost and time required for tunnel modifications were significantly reduced. Repeatability of pitot pressure measurements was excellent, and instrumentation errors were reduced by optimizing the pressure range of the transducers used for each test run. Bias errors in probe position prevented us from performing a successful in situ calibration of probe angle effects using pitot probes placed at an angle to the nozzle centerline.The abrupt throat geometry used in the Baseline and Configuration A and B nozzles modeled the throat geometry of the flight vehicle's spin motor nozzles. Survey data indicates that small ("unmeasurable") differences in the nozzle throat geometries produced measurable flow asymmetries and differences in the flow fields generated by supposedly identical nozzles. Therefore, data from the Baseline and Configuration A and B nozzles cannot be used for computational fluid dynamics (CFD) code validation.Configuration C and D nozzles replaced the abrupt throat geometry of Baseline and Configuration A and B nozzles with a 0.500-inch streamwise radius of curvature in the throat region. This throat geometry eliminated the flow asymmetries, flow separation in the nozzle throat, and measurable differences between the flow fields from identical nozzles that were observed in Baseline/A/B nozzles. Data from Configuration C and D nozzles can be used for CFD code validation.-4 -

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“…The problem is strongly vortical and has been extensively studied experimentally [18,19,21] (henceforth, collectively known as the "Beresh experiments"). The flowfield is dominated by a counter-rotating vortex pair, formed by a Kelvin-Helmholtz roll-up of the shear layer at the boundary between the jet and the crossflow.…”

Section: Introductionmentioning

confidence: 99%

“…Thereafter, we will sample the joint (C µ ,C ε2 ,C ε1 ) distribution to seed an ensemble of 100 3D JIC simulations. The ensemble results will provide a probabilistic prediction of the flowfield and we will check its accuracy against available JIC experimental data [18,19].…”

Section: Introductionmentioning

confidence: 99%

Tuning a RANS k-e model for jet-in-crossflow simulations.

Lefantzi¹,

Ray²,

Arunajatesan³

et al. 2013

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We develop a novel calibration approach to address the problem of predictive k − ε RANS simulations of jet-incrossflow. Our approach is based on the hypothesis that predictive k − ε parameters can be obtained by estimating them from a strongly vortical flow, specifically, flow over a square cylinder. In this study, we estimate three k − ε parameters, C µ , C ε2 and C ε1 by fitting 2D RANS simulations to experimental data. We use polynomial surrogates of 2D RANS for this purpose. We conduct an ensemble of 2D RANS runs using samples of (C µ ,C ε2 ,C ε1 ) and regress Reynolds stresses to the samples using a simple polynomial. We then use this surrogate of the 2D RANS model to infer a joint distribution for the k − ε parameters by solving a Bayesian inverse problem, conditioned on the experimental data. The calibrated (C µ ,C ε2 ,C ε1 ) distribution is used to seed an ensemble of 3D jet-in-crossflow simulations. We compare the ensemble's predictions of the flowfield, at two planes, to PIV measurements and estimate the predictive skill of the calibrated 3D RANS model. We also compare it against 3D RANS predictions using the nominal (uncalibrated) values of (C µ ,C ε2 ,C ε1 ), and find that calibration delivers a significant improvement to the predictive skill of the 3D RANS model. We repeat the calibration using surrogate models based on kriging and find that the calibration, based on these more accurate models, is not much better that those obtained with simple polynomial surrogates. We discuss the reasons for this rather surprising outcome.

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Penetration of a Transverse Supersonic Jet into a Subsonic Compressible Crossflow

Cited by 13 publications

References 43 publications

Transient interaction between a reaction control jet and a hypersonic crossflow

Transient interaction between a reaction control jet and a hypersonic crossflow

Experimental characterization of spin motor nozzle flow.

Tuning a RANS k-e model for jet-in-crossflow simulations.

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