Measuring Transition and Instabilities in a Mach 6 Hypersonic Quiet Wind Tunnel

Chynoweth, Brandon C.; Ward, Christopher A.; Schneider, Steven P.

doi:10.2514/6.2014-2643

Cited by 27 publications

(6 citation statements)

References 33 publications

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“…Overall, our extensive study has shown that roughness height is an important factor for the amplification/damping effect. For a second mode control design using 2-D roughness as in [29], the roughness height of 50% boundary layer thickness, width of 2 boundary layer thicknesss and spacing of 10 have been chosen. The results in [29] have shown that our design of 2-D roughness successfully damp the second mode.…”

Section: Summary and Discussionmentioning

confidence: 99%

“…Therefore, for the second mode control purpose, the roughness spacing of 10 is used to optimize the stabilization effect on the flow. An experiment of this 2-D roughness controlled second mode design had been applied to a flare cone in Mach 6 quiet tunnel at Purdue university [29]. Their experimental results show the our designed roughness strips have successfully damped the second mode waves.…”

Section: E the Effects Of Roughness Elements Spacingmentioning

confidence: 99%

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Stabilization of hypersonic boundary layer waves using 2-D surface roughness

Fong

Wang

Zhong

2013

43rd Fluid Dynamics Conference

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Recent research has shown that 2-D roughness of finite height can damp the second mode instability under certain conditions. For instance, it has been shown that the relative location of 2-D roughness element and the synchronization point is important in determining the 2-D roughness effect on modal growth. It was found that if a roughness element is placed downstream of a disturbance's synchronization point, the disturbance is damped. In this paper, an extensive DNS parametric study on the effect of second mode instability from roughness height, width and spacing between roughness elements are conducted. The results reveal that a taller roughness within one boundary layer thickness height results a stronger damping effect on the second mode. On the other hand, the roughness width effect is relatively insignificant compared with the height effect. Lastly, the spacing between roughness elements has been studied. The results show the increasing in spacing of roughness elements has both advantages and disadvantages. For the second mode control using 2-D roughness elements, roughness elements spacing of 10 times the roughness width has been shown to have the best overall damping effect in a broad frequency bandwidth. Overall, our extensive study has shown that roughness height is an important factor for the amplification/damping effect. For a second mode control design using 2-D roughness, the roughness height of 50% boundary layer thickness, width of 2 boundary layer thicknesss and spacing of 10 have been chosen to optimize the damping mechanism. Ideally the laminar-turbulent transition process can be divided into four stages. The first involves small disturbance fields which are initialized via a process termed "receptivity" by the viscous flow. The initial disturbance fields can involve both freestream and vehicle self-induced fluctuations such as acoustics, dynamic vortices, entropy spottiness, etc. The next stage is the linear growth stage, where small disturbances are amplified until they reach certain amplitude where nonlinear effects become important. The amplification can be in the form of exponential growth of eigenmodes (Tollmien-Schlichting waves or Mack waves) and non-modal growth of optimal disturbances (Transient growth). Once a disturbance has reached a finite amplitude, it often saturates and transforms the flow into a new, possibly unsteady state, which is termed as the secondary instability stage. The last

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Section: Summary and Discussionmentioning

confidence: 99%

Section: E the Effects Of Roughness Elements Spacingmentioning

confidence: 99%

Stabilization of hypersonic boundary layer waves using 2-D surface roughness

Fong

Wang

Zhong

2013

43rd Fluid Dynamics Conference

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“…The surface of the cone is assumed to be rigid, smooth, and isothermal in this study. This case is chosen because it is a benchmark that has been studied without roughness [24]. In the study of the smooth compression cone at the current freestream condition by Wheaton et al [22], no transition was observed, and the maximum N factor obtained from linear stability equation (LST) reached 14 at the end of the cone.…”

Section: A Test Model and Flow Conditionsmentioning

confidence: 99%

Second Mode Suppression in Hypersonic Boundary Layer by Roughness: Design and Experiments

Fong¹,

Wang²,

Huang³

et al. 2015

AIAA Journal

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“…The transition to turbulence is associated with both global and local changes to temperature occur on the cone followed by a decrease to near laminar levels [113].…”

Section: Potential Impact Of Transitional Boundary Layer On Structuramentioning

confidence: 99%

Interaction Between Aerothermally Compliant Structures and Boundary Layer Transition in Hypersonic Flow

Riley

2016

15th Dynamics Specialists Conference

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The use of thin-gauge, lightweight structures in combination with the severe aerothermodynamic loading makes reusable hypersonic cruise vehicles prone to fluidthermal-structural interactions. These interactions result in surface perturbations in the form of temperature changes and deformations that alter the stability and eventual transition of the boundary layer. The state of the boundary layer has a significant effect on the aerothermodynamic loads acting on a hypersonic vehicle.

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Measuring Transition and Instabilities in a Mach 6 Hypersonic Quiet Wind Tunnel

Cited by 27 publications

References 33 publications

Stabilization of hypersonic boundary layer waves using 2-D surface roughness

Stabilization of hypersonic boundary layer waves using 2-D surface roughness

Second Mode Suppression in Hypersonic Boundary Layer by Roughness: Design and Experiments

Interaction Between Aerothermally Compliant Structures and Boundary Layer Transition in Hypersonic Flow

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