Hypersonic Crossflow Instability

Kocian, Travis S.; Moyes, Alexander; Reed, Helen L.; Craig, Stuart A.; Saric, William S.; Schneider, Steven P.; Edelman, Joshua B.

doi:10.2514/1.a34289

Cited by 19 publications

(3 citation statements)

References 64 publications

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“…However, there still exist some difficulties. First, how to accurately predict the disturbance trajectory and the azimuthal wavelength variation along the trajectory are still open to question, although some progress has been made recently (Kocian et al 2019). Second, nonlinear interactions among multiple modes, which is essential in understanding the transition mechanism, cannot be tackled by local analyses since local modes may have different trajectories and thus may not interact.…”

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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“…( 2) is reached. The PSE and SIA methods have achieved great success in hypersonic boundary layers and tend to reveal that even though the unique second mode is present and dominant in high-speed flows, there are fundamental similarities in the nonlinear regime with the incompressible flows [70][71][72][73][74][75]. In fact, the second mode can interact with the first mode during the transition process and accelerate the energy transfer from the mainstream to the first mode, acting as a catalyst [76].…”

Section: Mechanisms Of Hypersonic Boundary Layer Transitionmentioning

confidence: 99%

Progress in physical modeling of compressible wall-bounded turbulent flows

Cheng,

Chen,

Zhu

et al. 2024

Acta Mech. Sin.

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Understanding, modeling and control of the high-speed wall-bounded transition and turbulence not only receive wide academic interests but also are vitally important for high-speed vehicle design and energy saving because transition and turbulence can induce significant surface drag and heat transfer. The high-speed flows share some fundamental similarities with the incompressible counterparts according to Morkovin’s hypothesis, but there are also significant distinctions resulting from multi-physics coupling with thermodynamics, shocks, high-enthalpy effects, and so on. In this paper, the recent advancements on the physics and modeling of high-speed wall-bounded transitional and turbulent flows are reviewed; most parts are covered by turbulence studies. For integrity of the physical process, we first briefly review the high-speed flow transition, with the main focus on aerodynamic heating mechanisms and passive control strategies for transition delay. Afterward, we summarize recent encouraging findings on turbulent mean flow scaling laws for streamwise velocity and temperature, based on which a series of unique wall models are constructed to improve the simulation accuracy. As one of the foundations for turbulence modeling, the research survey on turbulent structures is also included, with particular focus on the scaling and modeling of energy-containing motions in the logarithmic region of boundary layers. Besides, we review a variety of linear models for predicting wall-bounded turbulence, which have achieved a great success over the last two decades, though turbulence is generally believed to be highly nonlinear. In the end, we conclude the review and outline future works.

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“…The boundary layers over these two models are subject to strong cross-flow instability. For the yawed circular cone, Kocian et al (2019) reviewed elaborately the combined experimental and computational efforts on the cases at free-stream Mach numbers of around 6. The experimental facilities included two quiet wind tunnels, and the numerical techniques were NPSE and biglobal analyses.…”

Section: Introductionmentioning

confidence: 99%

Cross-flow vortices and their secondary instabilities in hypersonic and high-enthalpy boundary layers

Chen

Ren

et al. 2022

J. Fluid Mech.

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Compared to the streamwise instability, the cross-flow instability in high-enthalpy flows has received relatively less attention, but the latter is of vital importance in the flow transition for practical configurations. This work aims to investigate the cross-flow primary and secondary instabilities in hypersonic and high-enthalpy boundary layers, considering thermochemical non-equilibrium (TCNE) effects. The numerical tools adopted include a high-order shock-fitting solver, nonlinear parabolized stability equations and secondary instability theory (SIT). The flow over a swept parabola is calculated at a free-stream Mach number of 16. It is found that TCNE has a destabilizing effect on the cross-flow mode with a non-catalytic wall. Two important non-dimensional parameters are summarized to explain this effect. One is the ratio between the wall and boundary-layer edge temperatures, and the other is the cross-flow Mach number. Due to nonlinear effects, the stationary cross-flow vortices evolve and exhibit the classic rollover structures as in lower-speed flows. Two different disturbance energy norms are used in the energy budget analysis to classify the secondary cross-flow instability modes. The results from SIT highlight the importance of type-IV modes in TCNE flows at the downwash region of the vortex. The type-IV modes arise with the combined contribution from the wall-normal (on top and trough of the vortex) and spanwise (in the downwash region) production terms. The type-I mode is dominant in the calorically perfect gas case with an adiabatic wall, whereas the type-IV mode has the largest growth rate in the TCNE cases irrespective of wall temperature variation.

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Hypersonic Crossflow Instability

Cited by 19 publications

References 64 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

Progress in physical modeling of compressible wall-bounded turbulent flows

Cross-flow vortices and their secondary instabilities in hypersonic and high-enthalpy boundary layers

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