Numerical Investigation of Boundary-layer Transition Initiated by a Wave Packet for a Cone at Mach 6

Sivasubramanian, Jayahar; Fasel, Hermann F.

doi:10.2514/6.2010-900

Cited by 19 publications

(8 citation statements)

References 37 publications

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“…The fifth-order grid-centered upwind scheme has been extensively applied by Zhong's group at UCLA (Zhong & Ma 2006) to DNS studies of hypersonic boundary-layer receptivity and stability and strong shock-turbulence interactions (Rawat & Zhong 2010). Recently, grid-centered upwind schemes of up to ninth order were used by Sivasubramanian & Fasel (2010) for the nonlinear breakdown of supersonic and hypersonic boundary layers.…”

Section: High-order Finite-difference Methodsmentioning

confidence: 99%

“…The new methods were extended by Shukla & Zhong (2005) to a family of very-high-order nonuniform-grid compact finite-difference schemes with spatial order of accuracy ranging from fourth to twentieth. Recently, the nonuniform-grid highorder schemes were used by Sivasubramanian & Fasel (2010) to obtain stable boundary closures for their ninth-order schemes in the DNS of the hypersonic boundary-layer transition.…”

Section: Stable High-order Boundary Closure Schemesmentioning

confidence: 99%

“…Figure 11 shows the simulated turbulent spots for the Mach-5 case. More recently, Mayer et al (2011a) and Sivasubramanian & Fasel (2010) conducted a series of SDNS studies on the transition initiated by a localized disturbance in supersonic and hypersonic boundary layers over a flat plate and a circular sharp cone. For the case of Mach-6 flow over a sharp cone, the base flow was obtained by a separate simulation using a high-order finite-volume shock-capturing scheme.…”

Section: Transitional High-speed Boundary Layersmentioning

confidence: 99%

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Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Zhong

Wang

2012

Annu. Rev. Fluid Mech.

301

118

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The prediction of the laminar-turbulent transition of boundary layers is critically important to the development of hypersonic vehicles because the transition has a first-order impact on aerodynamic heating, drag, and vehicle operation. The success of transition prediction relies on a fundamental understanding of the relevant physical mechanisms. In the 20 years since the review by Kleiser & Zang (1991) on the direct numerical simulation (DNS) of the boundary-layer transition, significant progress has been made on DNS in the hypersonic flow regime and in the spatial DNS approach. Many high-order shock-capturing and shock-fitting finite-difference methods have been developed and extensively applied to numerical simulations of the hypersonic boundary-layer transition. DNS has become a powerful research tool and has led to discoveries of new transition mechanisms. This article reviews the recent progress of DNS on hypersonic boundary-layer receptivity, instability, and transition. The current status and future directions are also presented. 527 Annu. Rev. Fluid Mech. 2012.44:527-561. Downloaded from www.annualreviews.org by University of California -Los Angeles (Young Research Library) on 01/04/12. For personal use only. Receptivity mechanisms Transient growth B Increasing disturbance level Figure 1Paths to boundary-layer transition with respect to the disturbance amplitude. Path A, three-stage-transition mechanism in a weak-disturbance environment; path B, three-stage-transition mechanism including weak transient growth; paths C and D, transition mechanisms with strong transient growth; path E, bypass transition to very strong disturbance. Figure taken from Reshotko (

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Section: High-order Finite-difference Methodsmentioning

confidence: 99%

Section: Stable High-order Boundary Closure Schemesmentioning

confidence: 99%

Section: Transitional High-speed Boundary Layersmentioning

confidence: 99%

See 1 more Smart Citation

Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Zhong

Wang

2012

Annu. Rev. Fluid Mech.

301

118

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“…For reference purposes, the friction coefficient for a Blasius boundary layer 10) and a correlation by White (1991) To assess whether CASE 3 indeed predicts a representative streamwise skinfriction distribution independent of grid and time-averaging influences, and typical for an oblique breakdown transition scenario at Mach 3, the skin-friction coefficients of the other simulation cases (CASE 1-2, 4-6) listed in in the streamwise distribution of these modes in figure 5.13.…”

Section: Final Breakdown To Turbulencementioning

confidence: 99%

Numerical Simulation of Transition in Hypersonic Boundary Layers

Fasel¹,

Groß²,

Koevary³

et al. 2011

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The public reportmg burd en for th1s collection of mform ation is estimated to average 1 hour per response. includmg the tim e for rev>ewing instruct>ons. searclhing exi sting data so urces. gathering and mmnta1mng the data needed . and co mpleting and rev1ew 1 ng the collection of 1nforma t1 on. Send co mments regarding th1s burden est1m ate or any other aspect o fth1s collection of mformat1on . 1nclud1 ng suggesti ons for reduc1 ng the burden. to the Department of De fense. ExecutiV e Serv1ce D>rectorate (0704 -0 188) Respo ndents should be aware that notwithstanding any other prov1 s1 on of law. no person shall be sub;ect to any penalty for falling to comply w1th a collect> on of 1 nform at1on if 1 t does not display a currently v alid OMB co ntrol number PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ORGANIZATION. 1. REPORT DATE (DD-MM-YYYY)12. REPORT TYPE 3. DATES COVERED (From-To) SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Office of Scientific Research, AFOSR/RSA 4015 Wilson Blvd., Room 713, Arlington, VA 22203 SPONSOR/MONITOR'S REPORT NUMBER(S)AFRL-OSR-VA-TR-2012-0255 DISTRIBUTION/AVAILABILITY STATEMENTA -Approved For Public Release; Distribution is Unlimited. SUPPLEMENTARY NOTES ABSTRACTThe laminar-turbulent transition process in supersonic and hypersonic boillldary layers was investigated using spatial and temporal Direct Numerical Simulations (DNS). Our previous research indicated that oblique breakdown might be a highly relevant nonlinear mechanism for supersonic boillldary layers. However, a nonlinear mechanism would only be relevant for the transition process if this mechanism can lead to fully developed turbulence. Hence, to address this question, the late nonlinear transition regime of a supersonic flat-plate boillldary layer at Mach 3 was studied using spatial DNS. These simulations demonstrated that a fully turbulent flow can develop via oblique breakdown. We also investigated the nonlinear disturbance development in a hypersonic bolUldary layer on a sharp circular cone at Mach 8 using spatial and temporal DNS. It was confirmed in these simulations that fimdamental resonance and oblique breakdown are the viable paths to transition in hypersonic boillldary layers. 1S. SUBJECT TERMS

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“…To generate a disturbance of sufficiently broad spectrum, the boundary layer is pulsed through a small hole on the plate surface ahead of separation. This technique has been used by Sivasubramanian and Fasel for numerical studies of 3-D wave packets in hypersonic boundary layers on a flat plate [12] and cones [13][14][15][16][17]. Using a broad-spectrum forcing, it is feasible to simulate interference and selective amplification of various modes and thereby identify features of the disturbance evolution in different regions of the compression-corner flow.…”

mentioning

confidence: 99%

Direct Numerical Simulation of Wave Packets in Hypersonic Compression-Corner Flow

2016

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Direct numerical simulations of a three-dimensional wave packet propagating over a 5.5 deg compression corner at the freestream Mach number 5.373 are carried out. The Navier-Stokes equations are integrated using an implicit finite volume shock-capturing method with the second-order approximation in space and time. After computing the laminar flowfield, unsteady disturbances are imposed onto the steady solution via local suction blowing on the wall surface. The undisturbed boundary layer separates upstream of the corner and reattaches downstream, forming a shallow separation bubble. The suction-blowing pulse generates a three-dimensional wave packet propagating downstream. If the pulse is produced near the leading edge, the wave packet is dominated by oblique waves relevant to the first mode, whereas plane waves of the second mode are relatively small. At sufficiently strong forcing, the nonlinear effects destabilize the wave packet in the separation region and lead to its nonlinear breakdown downstream of the reattachment line. Ultimately, a young turbulent spot is formed in the reattached boundary layer. If the pulse is produced sufficiently far downstream of the leading edge, so that the major portion of the first-mode instability region is not involved, the wave packet is dominated by the second mode. These examples show that the wave-packet contents and its downstream evolution strongly depend on how and where the initial disturbance is excited.

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Numerical Investigation of Boundary-layer Transition Initiated by a Wave Packet for a Cone at Mach 6

Cited by 19 publications

References 37 publications

Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers

Numerical Simulation of Transition in Hypersonic Boundary Layers

Direct Numerical Simulation of Wave Packets in Hypersonic Compression-Corner Flow

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