Analysis of Crossflow Instability on HIFiRE-5 using Direct Numerical Simulation

Dinzl, Derek; Candler, Graham V.

doi:10.2514/6.2015-0279

Cited by 15 publications

(2 citation statements)

References 13 publications

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“…Nevertheless, Mack modes are observed to be substantially destabilized by cross-flow vortices in both cases. Dinzl & Candler (2015) emphasized the necessity of carefully considering the grid distribution and numerical schemes to obtain disturbance-free laminar flow for the HIFiRE-5 elliptic cone. They subsequently (Dinzl & Candler 2017) conducted direct numerical simulation (DNS) of evolution of stationary cross-flow vortices excited by the distributed roughness near the nose of the cone, and observed similar heat flux streak patterns as observed in experiments.…”

Section: Introductionmentioning

confidence: 99%

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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Section: Introductionmentioning

confidence: 99%

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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“…As has been noted in literature 18,19 the crossflow instability can be seeded even due to grid-to-grid roughness. This leads to distortion of the base state, and if the instability reaches an amplitude great enough to affect the stability analyses, may preclude meaningful results in the areas that are affected.…”

Section: Iva Crossflow Instabilitiesmentioning

confidence: 60%

Analysis of Windward Side Hypersonic Boundary Layer Transition on Blunted Cones at Angle of Attack

Tufts

Kimmel

2017

55th AIAA Aerospace Sciences Meeting

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Using Government drawings, specifications, or other data included in this document for any purpose other than Government procurement does not in any way obligate the U.S. Government. The fact that the Government formulated or supplied the drawings, specifications, or other data does not license the holder or any other person or corporation; or convey any rights or permission to manufacture, use, or sell any patented invention that may relate to them. This report was cleared for public release by the USAF 88th Air Base Wing (88 ABW) Public Affairs Office (PAO) and is available to the general public, including foreign nationals. Copies may be obtained from the Defense Technical Information Center (DTIC) (http://www.dtic.mil). AFRL-RQ-WP-TP-2017-0169 has been reviewed and is approved for publication in accordance with assigned distribution statement.

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Linear modal instabilities of hypersonic flow over an elliptic cone

et al. 2016

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Steady laminar flow over a rounded-tip $2\,:\,1$ elliptic cone of 0.86 m length at zero angle of attack and yaw has been computed at Mach number $7.45$ and unit Reynolds number $Re^{\prime }=1.015\times 10^{7}~\text{m}^{-1}$. The flow conditions are selected to match the planned flight of the Hypersonic Flight Research Experimentation HIFiRE-5 test geometry at an altitude of 21.8 km. Spatial linear BiGlobal modal instability analysis of this flow has been performed at selected streamwise locations on planes normal to the cone symmetry axis, resolving the entire flow domain in a coupled manner while exploiting flow symmetries. Four amplified classes of linear eigenmodes have been unravelled. The shear layer formed near the cone minor-axis centreline gives rise to amplified symmetric and antisymmetric centreline instability modes, classified as shear-layer instabilities. At the attachment line formed along the major axis of the cone, both symmetric and antisymmetric instabilities are also discovered and identified as boundary-layer second Mack modes. In both cases of centreline and attachment-line modes, symmetric instabilities are found to be more unstable than their antisymmetric counterparts. Furthermore, spatial BiGlobal analysis is used for the first time to resolve oblique second modes and cross-flow instabilities in the boundary layer between the major- and minor-axis meridians. Contrary to predictions for the incompressible regime for swept infinite wing flow, the cross-flow instabilities are not found to be linked to the attachment-line instabilities. In fact, cross-flow modes peak along most of the surface of the cone, but vanish towards the attachment line. On the other hand, the leading oblique second modes peak near the leading edge and their associated frequencies are in the range of the attachment-line instability frequencies. Consequently, the attachment-line instabilities are observed to be related to oblique second modes at the major-axis meridian. The linear amplification of centreline and attachment-line instability modes is found to be strong enough to lead to laminar–turbulent flow transition within the length of the test object. The predictions of global linear theory are compared with those of local instability analysis, also performed here under the assumption of locally parallel flow, where use of this assumption is permissible. Fair agreement is obtained for symmetric centreline and symmetric attachment-line modes, while for all other classes of linear disturbances use of the proposed global analysis methodology is warranted for accurate linear instability predictions.

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Analysis of Crossflow Instability on HIFiRE-5 using Direct Numerical Simulation

Cited by 15 publications

References 13 publications

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

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

Analysis of Windward Side Hypersonic Boundary Layer Transition on Blunted Cones at Angle of Attack

Linear modal instabilities of hypersonic flow over an elliptic cone

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