Stabilization of a Mach 5.92 Boundary Layer by Two-Dimensional Finite-Height Roughness

Le, Duan; Wang, Xiaowen; Zhong, Xiaolin

doi:10.2514/1.j051643

Cited by 48 publications

(27 citation statements)

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“…This study found that a series of panels, deformed into the flow, significantly disrupted the unstable growth of disturbances excited in the absence of the deformations. The potential for 2-D wavy walls to stabilize hypersonic boundary layers has also been observed for roughness scale deformations [23][24][25][26][27][28], in which the protuberances alter the local flowfield as opposed to introducing global pressure gradients.…”

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confidence: 89%

“…Boundary-layer stability is highly dependent on wall temperature [17,18] and surface geometry [18][19][20][21][22][23][24][25][26][27][28], both of which vary during flight for hot structure hypersonic vehicles. Previous studies have examined how aerothermoelastic effects, such as thermally induced deformations, can augment aerothermal loads [29,30] and impact boundary-layer transition [31,32].…”

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confidence: 99%

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Characterization of Structural Response to Hypersonic Boundary-Layer Transition

et al. 2016

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The inherent relationship between boundary-layer stability, aerodynamic heating, and surface conditions makes the potential for interaction between the structural response and boundary-layer transition an important and challenging area of study in high-speed flows. This paper phenomenologically explores this interaction using a fundamental two-dimensional aerothermoelastic model under the assumption of an aluminum panel with simple supports. Specifically, an existing model is extended to examine the impact of transition onset location, transition length, and transitional overshoot in heat flux and fluctuating pressure on the structural response of surface panels. Transitional flow conditions are found to yield significantly increased thermal gradients, and they can result in higher maximum panel temperatures compared to turbulent flow. Results indicate that overshoot in heat flux and fluctuating pressure reduces the flutter onset time and increases the strain energy accumulated in the panel. Furthermore, overshoot occurring near the midchord can yield average temperatures and peak displacements exceeding those experienced by the panel subject to turbulent flow. These results suggest that fully turbulent flow does not always conservatively predict the thermo-structural response of surface panels. Nomenclature b = compressibility exponent c = specific heat capacity c f = skin-friction coefficient E = modulus of elasticity F c = compressible flow transformation function h = panel thickness k = thermal conductivity L = panel length p = unsteady aerodynamic pressurẽ p = root-mean-square fluctuating pressure Q = aerodynamic heat flux q = dynamic pressure Re θ = momentum thickness Reynolds number T = temperature t = time t F = panel flutter onset time u = fluid velocity w = transverse panel displacement x = chordwise spatial coordinate x t = transition onset location x te = end of transition region x = spatial location nondimensionalized by panel length z = through-thickness spatial coordinate α = thermal expansion coefficient β = standard deviation γ = intermittency Δx t = transition length (x te − x t ) δ 1 = boundary-layer displacement thickness Θ = overall phase angle λ = viscosity/velocity power law exponent ν = Poisson's ratio ρ = panel density σ = spot propagation parameter τ = temporal phase angle ϕ = power spectral density ψ = spatial phase angle ω = angular frequency Subscripts avg = average e = boundary-layer edge lam = laminar max = maximum tran = transitional turb = turbulent VO = virtual origin

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Characterization of Structural Response to Hypersonic Boundary-Layer Transition

et al. 2016

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“…However, the corresponding growth mechanism differs from the one active downstream of a three-dimensional roughness investigated by Reshotko & Tumin (2004). Similarly, Duan, Wang & Zhong (2013) found for an adiabatic flat plate at Mach 6 that a two-dimensional wave can be destabilized or stabilized, qualitatively confirming earlier results by Marxen et al (2010). For a cone at Mach 5.85 with an adiabatic wall, Heitmann & Radespiel (2013) found by means of numerical simulations that the disturbance pressure amplitudes for a band of perturbations increase when a roughness element is present, again in accordance with the earlier findings of Marxen et al (2010).…”

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confidence: 94%

“…(a) (h, k) = (1, 0) case F (-) and case LIN2D (· · ·, -· -) and (b) (h, k) = (1/2, ±1) case LIN3D-S (· · ·, -· -).the roughness on disturbance amplification Marxen et al (2010). varied disturbance frequency with a fixed roughness position, whereasDuan et al (2013) achieved a similar effect by varying the position of the roughness for a fixed frequency.…”

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confidence: 98%

Nonlinear instability of a supersonic boundary layer with two-dimensional roughness

2014

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© © 2014 Cambridge University Press.Nonlinear instability in a supersonic boundary layer at Mach 4.8 with two-dimensional roughness is investigated by means of spatial direct numerical simulations (DNS). It was previously found that an important effect of a two-dimensional roughness is to increase significantly the amplitude of two-dimensional waves downstream of the roughness in a certain frequency band through enhanced instability and transient growth, while waves outside this band are damped. Here, we investigate the nonlinear secondary instability induced by a large-amplitude two-dimensional wave, which has received a significant boost in amplitude from this additional roughness-induced amplification. Both subharmonic and fundamental secondary excitation of the oblique secondary waves are considered. We found that even though the growth rate of the secondary perturbations increases compared to their linear amplification, only in some of the cases was a fully resonant state attained by the streamwise end of the domain. A parametric investigation of the amplitude of the primary wave, the phase difference between the primary and the secondary waves, and the spanwise wavenumber has also been performed. The transient growth experienced by the primary wave was found to not influence the secondary instability for most parameter combinations. For unfavourable phase relations between the primary and the secondary waves, the phase speed of the secondary wave decreases significantly, and this hampers its growth. Finally, we also investigated the strongly nonlinear stage, for which both the primary and the subharmonic secondary waves had a comparable, finite amplitude. In this case, the growth of the primary waves was found to vanish downstream of the transient growth region, resulting in a lower amplitude than in the absence of the large-amplitude secondary wave. This feedback also decreases the amplification rate of the secondary wave

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“…It should be noted that in the last years, the study of the stability of compressible boundary layers has been successful concerning the nonlinear wave interaction [11 15]. It is possible to indicate the results of numerical simulation in applying 2D roughness element for transition control in boundary layer at high supersonic speed [16]. Recent advances of numerical simulation for roughness-induced transition in high supersonic boundary layer are reviewed in [17].…”

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confidence: 99%

On the relative “receptivity” of twoand three-dimensional supersonic boundary layers to stationary disturbances at mach 2

Kosinov

Panina

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et al. 2015

Progress in Flight Physics – Volume 7

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Experiments on the in §uence of §at isolated square and diamond shaped roughness elements on the mean and pulsation characteristics of the boundary layer on a §at plate and a swept wing of comparable size are conducted. The shape of stickers has almost no e¨ect on the mass §ow pulsation amplitude in the trace of roughness. The relative ¤receptivity¥ of the three-dimensional (3D) boundary layer to stationary perturbations is approximately 1.5 times greater than the ¤receptivity¥ of the twodimensional (2D) boundary layer. The presence of roughness on the disturbance source line changes the pulsation spectra in 2D/3D boundary layer compared to the spectra in boundary layer on smooth surface.

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Stabilization of a Mach 5.92 Boundary Layer by Two-Dimensional Finite-Height Roughness

Cited by 48 publications

References 19 publications

Characterization of Structural Response to Hypersonic Boundary-Layer Transition

Characterization of Structural Response to Hypersonic Boundary-Layer Transition

Nonlinear instability of a supersonic boundary layer with two-dimensional roughness

On the relative “receptivity” of twoand three-dimensional supersonic boundary layers to stationary disturbances at mach 2

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