Design and performance of a hypersonic quiet wind tunnel at NUDT

Gang, Dundian; Yi, Shihe; Lu, Xiaoge

doi:10.2514/6.2017-2305

Cited by 8 publications

(2 citation statements)

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“…Hot streaks, such as those visualized in the BAM6QT, were also detected, as shown in őgure 15 [185]. Liu et al [173] used the hypersonic quiet wind tunnel at the National University of Defense Technology [191] to investigate the nonlinear evolution of the second Mack mode on a ŕared cone and reported the existence of high-frequency harmonics.…”

Section: Flows Over Flared Conesmentioning

confidence: 91%

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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Section: Flows Over Flared Conesmentioning

confidence: 91%

Görtler Instability and Transition in Compressible Flows

Xu,

Ricco,

Duan

2024

AIAA Journal

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“…8 To study hypersonic boundary layer transitions under low noise level conditions, hypersonic quiet wind tunnels were developed. 13,21,22 Although the noise level in these tunnels is much lower than that in a conventional hypersonic wind tunnel, the noise level is still higher than that in a real flight environment. In addition, because of the limited ranges available for the Mach number, the nozzle dimensions, and the Reynolds number, it is difficult for the hypersonic quiet wind tunnel to meet the requirements of hypersonic vehicle boundary layer transition testing.…”

Section: Introductionmentioning

confidence: 95%

Noise level effect on the hypersonic boundary layer

Sha

Yuan

Shi

et al. 2023

Advances in Mechanical Engineering

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The boundary layer state has a critical effect on hypersonic vehicle performance and the noise level is the main factor causing the differences between the boundary layer transition in a wind tunnel test and that in a real flight. The second mode wave frequency of the 7° half-angle cone models as measured in four hypersonic wind tunnels is collected. The effects of the noise level on the boundary layer are determined by comparing dimensionless parameters, which are nondimensionalized based on computed values. The results indicate that the noise level could affect the second mode wave frequency and the boundary layer thickness, where the second mode wave frequency decreases and the boundary layer thickness increases with increasing noise level. However, the mechanism by which the noise level influences the second mode wave frequency and the boundary layer thickness requires further study.

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Experimental study on hypersonic crossflow instability over a swept flat plate by flow visualization

Niu

Huo

et al. 2021

Acta Mech. Sin.

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Design and performance of a hypersonic quiet wind tunnel at NUDT

Cited by 8 publications

References 0 publications

Görtler Instability and Transition in Compressible Flows

Görtler Instability and Transition in Compressible Flows

Noise level effect on the hypersonic boundary layer

Experimental study on hypersonic crossflow instability over a swept flat plate by flow visualization

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