Boundary Layer Stability Analysis of HIFiRE-5b Flight Geometry

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

doi:10.2514/6.2017-4301

Cited by 12 publications

(13 citation statements)

References 11 publications

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“…In this work, three different models for the spatial wavenumber variation were employed and compared: the computed locally most amplified wavenumber of the stationary waves, a hybrid technique using computed vortex spreading (Moyes et al. 2017) anchored by experimentally observed wavenumbers, or the experimentally observed largest amplitude wavenumbers.…”

Section: Stability Analysis With Experimentally Observed Wavenumbersmentioning

confidence: 99%

“…The second technique determined the local spreading of neighbouring vortices based on the computed vortex pathlines (Moyes et al. 2017). In this approach, the basic state is adjusted to model the evolution of the wavenumber in the direction perpendicular to the marching path.…”

Section: Stability Analysis With Experimentally Observed Wavenumbersmentioning

confidence: 99%

“…While arbitrarily spaced disturbances can successfully excite disturbances of a given wavenumber, connecting the wavenumber of the controlled disturbance input to the wavenumber of instabilities at transition is not straightforward because the local wavenumber varies as the disturbances evolve downstream (Moyes et al. 2017). An open question in the research community, therefore, is how to accurately predict the wavenumber of the largest amplitude disturbances.…”

Section: Introductionmentioning

confidence: 99%

“…to compute the local effective wavenumber and implemented this on the HiFIRE-5 elliptic cone geometry (Moyes et al. 2017). Moyes et al.…”

Section: Introductionmentioning

confidence: 99%

“…This change in spacing, along with the local orientation of the disturbance path, was used to determine what the local effective wavenumber would be (Moyes et al. 2017). While these techniques more accurately modelled the changes in local wavenumber as the disturbances progressed downstream, they still cannot predict the actual wavenumber of the stationary cross-flow waves that would be observed experimentally or in flight.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Analysis of the hypersonic cross-flow instability with experimental wavenumber distributions

2019

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Section: Stability Analysis With Experimentally Observed Wavenumbersmentioning

confidence: 99%

Section: Stability Analysis With Experimentally Observed Wavenumbersmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…to compute the local effective wavenumber and implemented this on the HiFIRE-5 elliptic cone geometry (Moyes et al. 2017). Moyes et al.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Analysis of the hypersonic cross-flow instability with experimental wavenumber distributions

2019

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Boundary layer transition and linear modal instabilities of hypersonic flow over a lifting body

Chen

Dong

et al. 2022

J. Fluid Mech.

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Boundary layer transition over a lifting body of 1.6 m length at $2^\circ$ angle of attack has been simulated at Mach 6 and a unit Reynolds number $1.0 \times 10^7$ m $^{-1}$ . The model geometry is the same as the Hypersonic Transition Research Vehicle designed by the China Aerodynamics Research and Development Center. Four distinct transitional regions are identified, i.e. windward vortex region, shoulder vortex region, windward cross-flow region and shoulder cross-flow region. Multi-dimensional linear stability analyses by solving the two-dimensional eigenvalue problem (spatial BiGlobal approach) and the plane-marching parabolized stability equations (PSE3D approach) are further carried out to uncover the dominant instabilities in the last three regions as well as the shoulder attachment-line region. The shoulder vortex is conducive to both inner and outer modes of shear-layer instability, of which the latter most likely trigger the vortex breakdown. A novel method is presented to substantially reduce the computational cost of BiGlobal and PSE3D in resolving the cross-flow instabilities in cross-flow regions. The peak frequencies of cross-flow modes lie between 15 and 45 kHz. Whereas oblique second Mack modes are marginally unstable in the windward cross-flow region, they could be strong enough to compete with the cross-flow modes in the shoulder cross-flow region. In the shoulder attachment-line region, there exists only one unstable mode of Mack instability, differing from previous studies that show a hierarchy of modes in the context of symmetrical attachment-line flows. Results of the numerical simulation and multi-dimensional stability analyses are compared when possible, showing a fair agreement between the two approaches and highlighting the necessity of considering non-parallel effects.

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Transient growth analysis of hypersonic flow over an elliptic cone

et al. 2022

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Non-modal linear stability analysis results are presented for hypersonic flow over an elliptic cone with an aspect ratio of two at zero angle of attack, completing earlier modal instability analysis of flow around the same geometry. The theoretical framework to perform transient growth analysis of compressible flows on a generalized two-dimensional frame of reference is developed for the first time and is then applied to solve the initial-value problem governing non-modal linear instability on planes perpendicular to the cone axis, taken at successive streamwise locations along the elliptic cone. Parameter ranges examined here are chosen so as to model flight of the Hypersonic International Flight Research Experimentation 5 (HIFiRE-5) test geometry at altitudes of 21 km and 33 km, corresponding to Mach numbers 7.45 and 8.05 and unit Reynolds numbers $Re' = 1.07\times 10^7$ and $1.89\times 10^6$ , respectively. Results obtained indicate that the significance of the non-modal growth for laminar–turbulent transition increases with increasing flight altitude (decreasing Reynolds number). At a given set of flow parameters, transient growth is stronger in the vicinity of the tip of the cone and in azimuthal locations away from both of the minor (centreline) and major (attachment line) axes of the cone. Linear optimal disturbances calculated at conditions of maximal transient growth are found to peak in the crossflow region of the elliptic cone. These structures are elongated along the streamwise spatial direction, while being periodic along the spanwise direction with periodicity lengths of the same order of magnitude as the well-known structures identified as crossflow vortices in both experiments and simulations.

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Boundary Layer Stability Analysis of HIFiRE-5b Flight Geometry

Cited by 12 publications

References 11 publications

Analysis of the hypersonic cross-flow instability with experimental wavenumber distributions

Analysis of the hypersonic cross-flow instability with experimental wavenumber distributions

Boundary layer transition and linear modal instabilities of hypersonic flow over a lifting body

Transient growth analysis of hypersonic flow over an elliptic cone

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