Heat Transfer and Boundary-Layer Stability Analysis of Subscale BOLT and the Fin Cone

Mullen, Charles D.; Moyes, Alexander; Kocian, Travis S.; Reed, Helen L.

doi:10.2514/6.2019-3081

Cited by 9 publications

(4 citation statements)

References 14 publications

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“…14a is of interest. This result is consistent with the mean flow and boundary-layer stability analyses of Mullen et al [23]. A complete description of the numerical results in Fig.…”

Section: Off-body Measurementssupporting

confidence: 92%

“…The representative mean flow simulation for a quarter of the geometry given in Fig. 2 shows a buildup of flow near the center, which indicates that the flow moves inward, creating an opportunity for crossflow instabilities, which was validated computationally [21][22][23]. The mushroom-like structure contains stationary streamwise vortices, a similar effect seen on the HIFiRE-5 2:1 elliptic cone [24], which are dependent on Mach number and Reynolds number.…”

Section: B Bolt Flight Test Experimentsmentioning

confidence: 76%

“…11 is believed to be the result of noise radiating off the nozzle walls. The flow structure on the subscale BOLT model under quiet flow conditions was previously compared to DNS and computational fluid dynamics [23,25] with similar results between all groups. More results of the JHUAPL model in quiet and conventional flow can be found in Refs.…”

Section: A Flow Visualization and Heat Transfermentioning

confidence: 86%

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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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“…14a is of interest. This result is consistent with the mean flow and boundary-layer stability analyses of Mullen et al [23]. A complete description of the numerical results in Fig.…”

Section: Off-body Measurementssupporting

confidence: 92%

Section: B Bolt Flight Test Experimentsmentioning

confidence: 76%

Section: A Flow Visualization and Heat Transfermentioning

confidence: 86%

See 1 more Smart Citation

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

Kostak

Bowersox

2021

Journal of Spacecraft and Rockets

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“…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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Effect of forward-facing concavity on the aerodynamic and aerothermodynamic characteristics of an atmospheric Re-entry vehicle

Juhany,

Renganathan,

Varma

et al. 2024

Results in Engineering

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Heat Transfer and Boundary-Layer Stability Analysis of Subscale BOLT and the Fin Cone

Cited by 9 publications

References 14 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

Effect of forward-facing concavity on the aerodynamic and aerothermodynamic characteristics of an atmospheric Re-entry vehicle

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