Boundary-Layer Transition Measurements in a Mach-6 Quiet Tunnel

Ward, Christopher A.; Wheaton, Brad; Chou, Amanda; Gilbert, Peter; Steen, Laura; Schneider, Steven P.

doi:10.2514/6.2010-4721

Cited by 19 publications

(7 citation statements)

References 23 publications

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“…Except for Figures 6.27a (which illustrates the negligible effect of the step) and 6.25b, all TSP images through the large window are with the tapered paint edge. All hot-wire and PCB data except for the high-pressure runs were also recorded with the 'smooth'finish and tapered edge.Table 6.1 summarizes the paint roughness for all the TSP data.The Top Flite LustreKote spray paint has been used successfully for several subsequent TSP tests on various models[53]. Among the students in this research group, Chris Ward has the most experience applying this paint and found that the final paint thickness (mm) original step (simulated from gauge blocks) sanded step (profilometer measurement)…”

mentioning

confidence: 99%

Instability and Transition on the HIFiRE-5 in a Mach 6 Quiet Tunnel

Juliano

2010

40th Fluid Dynamics Conference and Exhibit

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confidence: 99%

Instability and Transition on the HIFiRE-5 in a Mach 6 Quiet Tunnel

Juliano

2010

40th Fluid Dynamics Conference and Exhibit

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“…The undisturbed boundary layer had a thickness of approximately 9.23 mm. Ward et al 20 measured the same instability with flush-mounted pressure transducers on the nozzle wall.…”

Section: Problem Statementmentioning

confidence: 94%

“…This will be accomplished by numerically simulating flow conditions similar to those of recent roughness experiments in the Boeing/AFOSR Mach 6 quiet wind tunnel at Purdue University. 19,20 The compressible Navier-Stokes equations are solved on a Cartesian grid using a fifth-order WENO scheme combined with a third-order cut-cell method to model the roughness. Twodimensional and three-dimensional test cases for the cut-cell method will be presented.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Hypersonic Flow Over an Isolated Roughness with a High-Order Cut-Cell Method

GreeneJeff

Eldredge

Zhong

et al. 2011

41st AIAA Fluid Dynamics Conference and Exhibit

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Results are presented for direct numerical simulations of hypersonic flow over an isolated roughness element located on a flat plate. The simulations were performed on a Cartesian grid with the roughness geometry imposed by a third-order cut-cell method. The simulations also utilize a fifth-order WENO scheme to capture any steep gradients in the flow created by the roughness. The combination results in a globally fourth-order scheme. Two-dimensional and three-dimensional test cases show very good agreement with results obtained from a body-fitted grid simulation. Preliminary results for Mach 6 flow over a k/δ = 0.75 cylindrical roughness are reported. In addition, results from a series of simulations of Mach 6 flow over a three-dimensional Gaussian roughness performed with a body-fitted grid are presented.

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“…Models of the optimal design were built and tested in the Boeing/AFOSR Mach-6 Quiet Tunnel (BAM6QT) at Purdue University. In the BAM6QT, Berridge et al [180,181] and Ward et al [172] used temperature-sensitive paint to detect the surface heat ŕux. As shown in őgure streaks', were observed under quiet conditions.…”

Section: Flows Over Flared Conesmentioning

confidence: 99%

Görtler Instability and Transition in Compressible Flows

Xu,

Ricco,

Duan

2024

AIAA Journal

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We present a discussion on theoretical, experimental, and computational research studies on Görtler instability and the related transition to turbulence occurring in compressible boundary layers over concave surfaces. We first examine the theoretical results on primary and secondary instabilities, emphasizing the role of receptivity, the mechanism by which external agents, such as freestream fluctuations or wall roughness, act on a boundary layer to trigger Görtler vortices. We review experimental findings obtained from measurements in supersonic and hypersonic wind tunnels and discuss studies employing numerical methods, focusing on the direct numerical simulation approach. The research in these two last sections is surveyed according to the geometrical configuration, from simple concave walls to more complex surfaces of hypersonic vehicles. The experimental investigations have been successful in the visualizations of Görtler vortices, in the measurement of the wall-heat transfer in the transitional region, and in the computation of the Görtler-vortex growth rates, although detailed boundary-layer velocity measurements are still missing. Direct numerical simulations have confirmed instability results emerging from stability theories and revealed nonlinear interactions between Görtler vortices and other disturbances. The established initial-boundary-value receptivity theory can certainly benefit from more advanced experimental measurements, and receptivity results should be used in combination with direct numerical simulations. A major conclusion of our review is therefore that the understanding of Görtler vortices should be pursued by a combined methodology including theoretical analysis based on the receptivity formalism, direct numerical simulation, and experiments. Highly desirable outcomes of such endeavor are the prediction of the location and extension of the transition region, and a model for the transition process. We finally highlight further prospects and challenges on fundamental and applied research on Görtler instability and transition in compressible flows.

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Boundary-Layer Transition Measurements in a Mach-6 Quiet Tunnel

Cited by 19 publications

References 23 publications

Instability and Transition on the HIFiRE-5 in a Mach 6 Quiet Tunnel

Instability and Transition on the HIFiRE-5 in a Mach 6 Quiet Tunnel

Numerical Study of Hypersonic Flow Over an Isolated Roughness with a High-Order Cut-Cell Method

Görtler Instability and Transition in Compressible Flows

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