Instabilities in Mach 6 Flow over a Cone with a Swept Fin

Knutson, Anthony; Sidharth, G. S.; Candler, Graham V.

doi:10.2514/6.2018-3071

Cited by 14 publications

(3 citation statements)

References 33 publications

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“…14 is provided in Refs. [25,27,45]. In summary, these plots show how the flow instabilities, indicated by larger fluctuation levels, are coupled to the secondary flow structure.…”

Section: Off-body Measurementsmentioning

confidence: 85%

Preflight Ground Test Analyses of the Boundary Layer Transition (BOLT) Flight Geometry

Kostak

Bowersox

2021

Journal of Spacecraft and Rockets

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heating was quantified using infrared thermography. Under quiet conditions, heat flux was characterized by a streak structure with no transition observed. Transition was observed within the conventional noise ACE facility in two regions: 1) in the vicinity of a mixed-mode structure and 2) in an outboard traveling crossflow region. The flow structure within a coherent vortex rollup located off centerline was further characterized under quiet flow conditions with constant-temperature hot-wire anemometry and high-frequency surface-pressure spectra. The measured mean and disturbance flow structure were in qualitative agreement with the simulations. The hot-wire spectral content showed growth in the 25-40 kHz range, which also agreed with the simulations. Surface-pressure spectral results showed similar growth in the 25-50 kHz range observed under both quiet and conventional freestream conditions.

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“…14 is provided in Refs. [25,27,45]. In summary, these plots show how the flow instabilities, indicated by larger fluctuation levels, are coupled to the secondary flow structure.…”

Section: Off-body Measurementsmentioning

confidence: 85%

Preflight Ground Test Analyses of the Boundary Layer Transition (BOLT) Flight Geometry

Kostak

Bowersox

2021

Journal of Spacecraft and Rockets

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“…Over the last two decades, a number of methods for predicting the initial growth of boundary-layer instabilities on complex shapes in hypersonic flow have been developed. These methods include spatial BiGlobal analysis [14,15], plane-marching PSE [16,17], One-Way Navier Stokes (OWNS) [18], linearized Direct Numerical Simulation (LDNS) [19], forced DNS coupled with sparsity-promoting Dynamic Mode Decomposition [20], Wavepacket Tracking with Adaptive Mesh Refinement (AMR-WPT) [21], and Input/Output (I/O) analysis [22]. All of these methods are linear and 2 Distribution Statement A: Approved for Public Release; Distribution Unlimited.…”

Section: Introductionmentioning

confidence: 99%

“…Both of these flow features complicate the computational analysis due to the spanwise distortion of the laminar flow. Several groups have made progress over the last few years in studying the surface heating and boundary-layer stability characteristics of various fin-cone configurations tested at Purdue [20,[27][28][29][30][31][32][33]. From this prior analysis, it was clear that streamwise-aligned laminar vortices played an important role in the transition process along the cone, but the question of how to interpret the results of different linear stability analysis methods when applied to this complex flow field remained unclear.…”

Section: Introductionmentioning

confidence: 99%

Assessment of Linear Methods for Analysis of Boundary Layer Instabilities on a Finned Cone at Mach 6

Araya

Bitter

Wheaton

et al. 2022

AIAA AVIATION 2022 Forum

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Boundary-layer instabilities for a finned cone at Mach = 6, Re = 8.4 × 10 6 [ −1 ], and zero incidence angle are examined using linear stability methods of varying fidelity and maturity, following earlier analysis presented in [1]. The geometry and laminar flow conditions correspond to experiments conducted at the Boeing Air Force Mach 6 Quiet Tunnel (BAM6QT) at Purdue University. Where possible, a common mean flow is utilized among the stability computations, and comparisons are made along the acreage of the cone where transition is first observed in the experiment. Stability results utilizing Linear Stability Theory (LST), planar Parabolized Stability Equations (planar-PSE), One-Way Navier Stokes (OWNS), forced direct numerical simulation (DNS), and Adaptive Mesh Refinement Wavepacket Tracking (AMR-WPT) are presented. A dominant three-dimensional vortex instability occurring at ≈ 250 kHz is identified that correlates well with experimental measurements of transition onset. With the exception of LST, all of the higher-fidelity linear methods considered in this work were consistent in predicting the initial growth and general structure of the vortex instability as it evolved downstream. Some of the challenges, opportunities, and development needs of the stability methods considered are discussed.

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Numerical Simulation of Instabilities in the Boundary-Layer Transition Experiment Flowfield

Knutson

Thome

Candler

2021

Journal of Spacecraft and Rockets

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Instabilities in Mach 6 Flow over a Cone with a Swept Fin

Cited by 14 publications

References 33 publications

Preflight Ground Test Analyses of the Boundary Layer Transition (BOLT) Flight Geometry

Preflight Ground Test Analyses of the Boundary Layer Transition (BOLT) Flight Geometry

Assessment of Linear Methods for Analysis of Boundary Layer Instabilities on a Finned Cone at Mach 6

Numerical Simulation of Instabilities in the Boundary-Layer Transition Experiment Flowfield

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