Response of a hypersonic blunt cone boundary layer to slow acoustic waves with assessment of various routes of receptivity

Su, Caihong; Luo, Juan; Wan, Baikun

doi:10.1007/s10483-018-2391-6

Cited by 22 publications

(4 citation statements)

References 23 publications

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“…Since blunt cone is an aerodynamic configuration existing extensively in hypersonic vehicle, it was chosen as the computing model in many studies on the receptivity characteristics of hypersonic boundary layer (Zhang et al 2008;Prakash et al 2011;Wan et al 2018). So, a blunt cone with 8° half-cone angle and 6 Mach freestream is introduced in this paper.…”

Section: Computational Conditions and Modelmentioning

confidence: 99%

Numerical Investigation on the Response Characteristics of Hypersonic Boundary Layer under Different Types of Finite Amplitude Pulse Disturbance Waves

2021

JAFM

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The hypersonic transient flow pass a blunt cone under three types of pulse disturbances is calculated using DNS. The response characteristic of hypersonic boundary layer among different types of pulse disturbance is compared. The distribution and evolution characteristics of disturbance modes are investigated by mode analysis. Results indicate that the receptivity characteristics induced by freestream pulse wave have both similarities and differences with that induced by freestream continuous wave. The interactions of different types of pulse waves with boundary layer and bow shock present different characteristics. The boundary layer thermodynamic characteristics under pulse fast acoustic wave are sensitive to mainstream disturbance wave, and that under pulse slow acoustic wave are sensitive to residual reflection wave. The type of pulse disturbance wave has a great influence on the production and mode distribution of boundary layer disturbance wave. In general, the disturbance amplitude in the pulse fast acoustic wave situation is the largest, the case of entropy wave is the second, and the case of slow acoustic wave is the smallest. For regional influence, the type of pulse disturbance has a huge impact on the disturbance modes in both the head and the non-head. For the three cases of pulse wave, the main mode group attenuation phenomenon which narrows the disturbance frequency band exists in the boundary layer. This group attenuation is the fastest for freestream slow acoustic wave, followed by entropy wave, and then fast acoustic wave. Under the action of pulse slow acoustic waves, the disturbance wave evolution of each order mode in the boundary layer along the streamwise is relatively stable, followed by entropy wave, and the case of fast acoustic wave is the most active.

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Section: Computational Conditions and Modelmentioning

confidence: 99%

Numerical Investigation on the Response Characteristics of Hypersonic Boundary Layer under Different Types of Finite Amplitude Pulse Disturbance Waves

2021

JAFM

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“…The receptivity in the presence of a shock has been investigated primarily using DNS in [49][50][51]62], among others, with the focus being primarily on the leading-edge adjustment. For the boundary layer over a cone, the DNS of the receptivity to acoustic waves suggest that the slow acoustic waves and entropy-layer disturbances after a bow shock play a key role for the excitation of first and second modes, respectively [63,64]. However, the precise scale tuning mechanisms are yet to be identified, which necessarily requires careful asymptotic analyses.…”

Section: Introductionmentioning

confidence: 99%

Receptivity of inviscid modes in supersonic boundary layers to wall perturbations

Liu

Dong

2021

J Eng Math

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The present paper investigates the receptivity of inviscid first and second modes in a supersonic boundary layer to time-periodic wall disturbances in the form of local blowing/suction, streamwise velocity perturbation and temperature perturbation, all introduced via a small forcing slot on the flat plate. The receptivity is studied using direct numerical simulations (DNS), finite- and high-Reynolds-number approaches, which complement each other. The finite-Reynolds-number formulation predicts the receptivity as accurately as DNS, but does not give much insight to the detailed excitation process, nor can it explain the significantly weaker receptivity efficiency of the streamwise velocity and temperature perturbations relative to the blowing/suction. In order to shed light on these issues, an asymptotic analysis was performed in the limit of large Reynolds number. It shows that the receptivity to all three forms of wall perturbations is reduced to the same mathematical form: the Rayleigh equation subject to an equivalent suction/blowing velocity, which can be expressed explicitly in terms of the physical wall perturbations. Estimates of the magnitude of the excited eigenmode can be made a priori for each case. Furthermore, the receptivity efficiencies for the streamwise velocity and temperature perturbations are quantitatively related to that for the blowing/suction by simple ratios, which are of $$O(R^{-1/2})$$ O ( R - 1 / 2 ) and have simple expressions, where R is the Reynolds number based on the boundary-layer thickness at the centre of the forcing slot. The simple leading-order asymptotic theory predicts the instability and receptivity characteristics accurately for sufficiently large Reynolds numbers (about $$10^4$$ 10 4 ), but appreciable error exists for moderate Reynolds numbers. An improved asymptotic theory is developed by using the appropriate impedance condition that accounts for the $$O(R^{-1/2})$$ O ( R - 1 / 2 ) transverse velocity induced by the viscous motion in the Stokes layer adjacent to the wall. The improved theory predicts both the instability and receptivity at moderate Reynolds numbers ($$R=O(10^3)$$ R = O ( 10 3 ) ) with satisfactory accuracy. In particular, it captures well the finite-Reynolds-number effects, including the Reynolds-number dependence of the receptivity and the strong excitation occurring near the so-called synchronisation point.

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“…所谓熵层是由于钝头体前弓形激波的激波角变化较大, 在激波后形成高熵梯度区 [22][23][24] . Stetson等人 [25] 通过实验研究发现, 熵层内扰动幅值较大, 且保持缓慢地增长.…”

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“…Stetson等人 [25] 通过实验研究发现, 熵层内扰动幅值较大, 且保持缓慢地增长. 后来通过线性稳定性分析得到熵层不稳定性模态, 其增长率非常小, 与实验结果相一致 [20,21,23,26] .…”

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Recent progresses on hypersonic boundary-layer transition

Chen

Yuan

et al. 2019

Sci. Sin.-Phys. Mech. Astron.

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Response of a hypersonic blunt cone boundary layer to slow acoustic waves with assessment of various routes of receptivity

Cited by 22 publications

References 23 publications

Numerical Investigation on the Response Characteristics of Hypersonic Boundary Layer under Different Types of Finite Amplitude Pulse Disturbance Waves

Numerical Investigation on the Response Characteristics of Hypersonic Boundary Layer under Different Types of Finite Amplitude Pulse Disturbance Waves

Receptivity of inviscid modes in supersonic boundary layers to wall perturbations

Recent progresses on hypersonic boundary-layer transition

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