RANS modeling of high-speed aerodynamic flow transition with consideration of stability theory

Fu, Song; Wang, Liang

doi:10.1016/j.paerosci.2012.08.004

Cited by 104 publications

(17 citation statements)

References 135 publications

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“…Generally, a Global (BiGlobal or TriGlobal) [5,6] or Local stability problem [7] may be formulated in accordance with the number of dimensions of the prescribed basic flow. The LST, in a different aspect, helps to build the transition model for engineering applications [8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Study of the Discrete Spectrum in a Mach 4.5 Görtler Flow

Ren

2014

Flow Turbulence Combust

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Evolution of the discrete spectrum in the Ma = 4.5 boundary layer is studied with LST and PSE approaches. Both two-dimensional (2-D) and three-dimensional (3-D) disturbances are considered with streamwise curvature effects. The concave curvature shows a destabilizing effect on the 2-D second/third mode when the fast mode (mode F (1) , mode F (2) ...) synchronizes with the slow mode (mode S). The spectrum branching in the synchronization between the mode F (2) and mode S is also observed. The increase in the spanwise wavenumber(3-D disturbances), on the other hand, suppresses the synchronization between mode F and mode S and reduces the growth rate of the unstable mode. With regard to the 3-D disturbances subjecting to the concave curvature, the mode S originating from the slow acoustic wave amounts to the unsteady Görtler mode while the quasi-steady Görtler mode emanates from the continuous spectrum of the vorticity/entropy wave.

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Section: Introductionmentioning

confidence: 99%

Study of the Discrete Spectrum in a Mach 4.5 Görtler Flow

Ren

2014

Flow Turbulence Combust

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“…The compressibility corrections have been carefully examined for their effects on a hypersonic validation database. With the use of SST model with the compressibility corrections, the present authors have conducted high-speed simulations with a reasonably wide range of Mach number (2,(34)(35)(36)(37)(38) , such as supersonic and hypersonic flows past cones at small incidences and elliptic cones at zero incidences. The objective of this work is thus to simulate supersonic/hypersonic flows over a flat plate with transitionally and fully rough surface, by using the SST model with advanced compressibility as well as roughness corrections.…”

Section: March 2017mentioning

confidence: 99%

Computational study of drag increase due to wall roughness for hypersonic flight

Wang

Zhao

2017

Aeronaut. j.

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In this study, a series of numerical experiments are performed on supersonic/hypersonic flows over an adiabatic flat plate with transitionally and fully rough surfaces. The Mach numbers simulated are 4, 5, 6, and 7; the flight heights considered are 20, 24, 28, 32, and 36 km. First, a modified roughness correction is proposed and validated with the measured data for low-speed flat-plate cases. It is verified that for the equivalent sand grain heights in the intermediate and fully rough regimes, there is a good agreement with the semi-empirical formula available in the open literature. Then, this roughness correction is applied to high-speed flow regime to investigate the effects of flight heights and Mach numbers on drag for rough-wall flat-plate cases. It is found that within the roughness measured in real flight, the roughness height change has little effect on drag compared to the variations of both flight heights and Mach numbers. The drag coefficient derivation between rough-wall and smooth-wall conditions, achieves the maximum value of 0.79% for the 60 cases selected.

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“…For this purpose, transport equation approaches have been developed, for example, transition closure or transition/turbulence models [67][68][69][70][71][72][73][74] based on the modeling of non-turbulent fluctuations existing upstream of the point of transition onset. In these types of models the development of the modelled non-turbulent fluctuations and their impact on the flow is followed until a model-specific threshold has been reached.…”

Section: Transport Equation Approachesmentioning

confidence: 99%