Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Sivasubramanian, Jayahar

doi:10.2514/6.2011-3562

Cited by 16 publications

(6 citation statements)

References 101 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It seems that transition may occur near x = 0.44m, when the heat-transfer rises for the second time. This complex behavior was very surprising when first measured, but yields good qualitative agreement with the computations by Fasel's group for similar geometries [58,91,92]. However, quantitative comparisons remain to be obtained.…”

Section: Effects Of Tunnel Noise On the Nonlinear Breakdownmentioning

confidence: 59%

See 1 more Smart Citation

Developing Mechanism-Based Methods for Estimating Hypersonic Boundary-Layer Transition in Flight: The Role of Quiet Tunnels

Schneider

2013

43rd Fluid Dynamics Conference

View full text Add to dashboard Cite

For more than half a century, researchers have been aware that freestream fluctuations have an important effect on laminar-turbulent transition. A century of effort has also been devoted to the development of theory and experiment for the instability mechanisms that lead to transition, in order to develop more reliable prediction methods. Both of these long efforts are now beginning to bear fruit in the subarea of hypersonic transition. At hypersonic speeds, it was necessary to develop quiet tunnels with laminar nozzle-wall boundary layers in order to achieve low fluctuation levels that are comparable to flight; three such tunnels are now in operation, worldwide. Hypersonic instability mechanisms are also more complex than at low speeds, and the computer resources and computational tools necessary to compute them are only now becoming fairly widely available, along with the instrumentation necessary to measure these mechanisms in a reasonably affordable way. The present review begins to show how these two steps are aiding in the development of physics-based methods for estimating transition in flight.

show abstract

Section: Effects Of Tunnel Noise On the Nonlinear Breakdownmentioning

confidence: 59%

“…At what conditions do the waves begin to break down to turbulence? Direct numerical simulations are beginning to become available, but these must make many assumptions [58,59]. Certainly one would expect tunnel noise to affect the nonlinear breakdown as well as the initial amplitude, but can the effect of tunnel noise be sorted out?…”

Section: Overall Conceptsmentioning

confidence: 98%

Developing Mechanism-Based Methods for Estimating Hypersonic Boundary-Layer Transition in Flight: The Role of Quiet Tunnels

Schneider

2013

43rd Fluid Dynamics Conference

View full text Add to dashboard Cite

show abstract

“…The research group of Fasel investigated laminar-turbulent transition using high-fidelity direct numerical simulations. The objective was to conduct DNS in close collaboration with other experimental and computational efforts to identify relevant mechanisms, especially the nonlinear breakdown mechanisms [54,73] The calculations of nonlinear wave interactions [99,153,154,155], the Gaster wave packet [149,150,151,152] and turbulent spot [148] in a hypersonic boundary layer were remarkable because of the similarities with incompressible flow. This offers some promise that tackling the breakdown of hypersonic boundary layers is not as formidable as once thought.…”

Section: Spatial Dns Of Breakdown (Hermann Fasel)mentioning

confidence: 99%

Integrated Theoretical, Computational, and Experimental Studies for Transition Estimation and Control

Saric¹,

Bowersox²,

Reed³

et al. 2014

Self Cite

View full text Add to dashboard Cite

“…a canonical shape) is generally a first choice. The sharp cone with a circular cross-section has been the subject of many theoretical/computational [9][10][11][12][13][14][15][16][17] and experimental [18][19][20][21][22][23][24][25][26][27][28][29][30][31][32][33][34][35][36] investigations. It should be noted that most of the experimental work carried out for the conical geometry has been performed in "cold" flow tunnels with very low static free-stream temperatures (see for example, Stetson et al [18][19][20][21][22] , Stetson and Kimmel 24-26 , Bountin 29 , Alba et al 30 , Hofferth et al, 31 Lachowicz et al, 37,38 Schneider, 39 and Berridge et al 3 ).…”

Section: Introductionmentioning

confidence: 99%

Linearized Navier-Stokes Simulations of the Spatial Stability of a Hypersonic Boundary-Layer on a Flared Cone

Salemi

Fasel²

2015

53rd AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

The linear stability of a hypersonic boundary-layer is investigated for an almost sharp flared cone at Mach 6. Towards this end, a short-duration pulse through a small hole on the surface of the cone is utilized to excite a broad spectrum of frequencies and streamwise wave numbers in an axisymmetric domain. The flow conditions chosen are from the lowenthalpy experiments performed at the Boeing/AFOSR Mach-6 Quiet Tunnel (BAM6QT) at Purdue University. 1-3 In the present work, the newly developed version of the Linearized Compressible Navier-Stokes solver (LinCS) 4-6 using generalized cylindrical coordinates is introduced. The derivation of the linearized equations is presented along with results which were generated using the Linearized Compressible Navier-Stokes solver (LinCS) and Direct Numerical Simulations (DNS) for the aforementioned conditions. This new version of LinCS was verified for the linear regime with the Parabolized Stability Equations (PSE) results presented in the literature, 2 and our low amplitude DNS calculations. In addition, our previous DNS results 6 for a 5 deg straight cone in a high-enthalpy flow indicated that, in the linear regime, oscillations in the phase speed, growth rate, wave number and Nfactor are observed as amplified second mode wave components synchronize with different boundary layer modes( i.e. entropy/vorticity and acoustic modes). 7 Also, such oscillations cease before an amplified wave component slows down to the same phase speed as the vorticity/entropy waves. Our present simulations show that a similar phenomenon is also present in the case of a low-enthalpy flow on a flared cone.

show abstract

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Cited by 16 publications

References 101 publications

Developing Mechanism-Based Methods for Estimating Hypersonic Boundary-Layer Transition in Flight: The Role of Quiet Tunnels

Developing Mechanism-Based Methods for Estimating Hypersonic Boundary-Layer Transition in Flight: The Role of Quiet Tunnels

Integrated Theoretical, Computational, and Experimental Studies for Transition Estimation and Control

Linearized Navier-Stokes Simulations of the Spatial Stability of a Hypersonic Boundary-Layer on a Flared Cone

Contact Info

Product

Resources

About