Leading-edge receptivity of a hypersonic boundary layer on a flat plate

Маслов, А. А.; Shiplyuk, A. N.; Sidorenko, A. A.; Arnal, D.

doi:10.1017/s0022112000002147

Cited by 140 publications

(111 citation statements)

References 20 publications

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“…For the flow over the flat plate, three sets of grid structures are used to check the grid independence of numerical simulation results near the leading edge. The steady flow is compared with the experimental measurements of Maslov et al [29]. At three different locations, x 96, 121, and 138 mm (R 1134:46, 1254.19, and 1329.66); the distributions of the dimensionless streamwise velocity and normalized Mach number in the wall-normal direction are in good agreement with those measured in experiments.…”

Section: Direct Numerical Simulation Approachsupporting

confidence: 58%

Numerical Simulation and Theoretical Analysis of Perturbations in Hypersonic Boundary Layers

2011

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Direct numerical simulations on the receptivity of hypersonic boundary layers over a flat plate and a sharp wedge were carried out with two-dimensional periodic-in-time wall blowing-suction introduced into the flow through a slot. The freestream Mach numbers were equal to 5.92 and 8 in the cases of the adiabatic flat plate and sharp wedge, respectively. The perturbation flowfield was decomposed into normal modes with the help of the multimode decomposition technique based on the spatial biorthogonal eigenfunction system. The decomposition allowed for the filtering out of stable and unstable modes hidden behind perturbations of another physical nature.

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Section: Direct Numerical Simulation Approachsupporting

confidence: 58%

Numerical Simulation and Theoretical Analysis of Perturbations in Hypersonic Boundary Layers

2011

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“…Fast modes do undergo decay and hence the receptivity to fast sound waves should be relatively weaker. Fedorov (2003) made detailed comparison with the experimental data of Maslov et al (2001) and observed reasonably good agreement for planar or moderately three-dimensional disturbances, but the prediction deteriorates and even exhibits opposite trends when three-dimensionality becomes sufficiently strong. Indeed, highly oblique instability modes with spanwise wavenumbers β > √ M 2 − 1 α have phase speeds much smaller than the free-stream velocity and acquire a triple-deck structure (Smith 1989), where α is the streamwise wavenumber.…”

Section: Introductionmentioning

confidence: 92%

“…All these observations testify the crucial role of receptivity. However, there have been just a few detailed measurements of receptivity using controlled free-stream disturbances, and these were conducted by Maslov et al (2001) and Semionov & Kosinov (1999, 2008 for flat plates with sharp and blunt leading edges.…”

Section: Introductionmentioning

confidence: 99%

Response and receptivity of the hypersonic boundary layer past a wedge to free-stream acoustic, vortical and entropy disturbances

Qin

2016

J. Fluid Mech.

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This paper analyses the response and receptivity of the hypersonic boundary layer over a wedge to free-stream disturbances including acoustic, vortical and entropy fluctuations. Due to the presence of an attached oblique shock, the boundary layer is known to support viscous instability modes whose eigenfunctions are oscillatory in the far field. These modes acquire a triple-deck structure. Any of three elementary types of disturbances with frequency and wavelength on the triple-deck scales interacts with the shock to generate a slow acoustic perturbation, which is reflected between the shock and the wall. Through this induced acoustic perturbation, vortical and entropy free-stream disturbances drive significant velocity and temperature fluctuations within the boundary layer, which is impossible when the shock is absent. A quasi-resonance was identified, due to which the boundary layer exhibits a strong response to a continuum of high-frequency disturbances within a narrow band of streamwise wavenumbers. Most importantly, in the vicinity of the lower-branch neutral curve the slow acoustic perturbation induced by a disturbance of suitable frequency and wavenumbers is in exact resonance with a neutral eigen mode. As a result, the latter can be generated directly by each of three types of free-stream disturbances without involving any surface roughness element. The amplitude of the instability mode is determined by analysing the disturbance evolution through the resonant region. The fluctuation associated with the eigen mode turns out to be much stronger than free-stream disturbances due to the resonant nature of excitation and in the case of acoustic disturbances, to the well-known amplification effect of a strong shock. Moreover, excitation at the neutral position means that the instability mode grows immediately without undergoing any decay, or missing any portion of the unstable region. All these indicate that this new mechanism is particularly efficient. The boundary-layer response and coupling coefficients are calculated for typical values of parameters.

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“…It reveals the physics of local receptivity associated with diffraction and scattering of acoustic waves near the leading edge of the plate. In [4], these theoretical results are compared with the experimental data [5] and numerical calculations [6].…”

Section: Introductionmentioning

confidence: 99%

“…The angles of inclination of 0 and ± 45 ° with respect to the plate are considered. In [13], the results for these angles were compared with the results of the asymptotic theory [5,6]. In [14], calculations of the receptivity of the boundary layer to fast and slow acoustic waves at M=4.5.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of the supersonic boundary layer interaction with arbitrary oriented acoustic waves

Семенов

Гапонов

2017

AIP Conference Proceedings

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Abstract. Based the direct numerical simulation in the paper the supersonic flow around of the infinitely thin plate, which was perturbed by the acoustic wave, was investigated. Calculations carried out in the case of small perturbations at the Mach number M=2 and Reynold's numbers Re<600. It is established that the velocity perturbation amplitude within the boundary layer is greater than the amplitude of the external acoustic wave in several times, the maximum amplitude growth is reached 10. At the small sliding and incidence angles the velocity perturbations amplitude increased monotonously with Reynold's numbers. At rather great values of these angles there are maxima in dependences of the velocity perturbations amplitude on the Reynold's number. The oscillations exaltation in the boundary layer by the sound wave more efficiently if the plate is irradiated from above. At the fixed Reynolds's number and frequency there are critical values of the sliding and incidence angles (χ, φ) at which the disturbances excited by a sound wave are maxima. At M=2 it takes place at χ≈ φ ≈30°. The excitation efficiency of perturbations in the boundary layer increases with the Mach number, and it decreases with a frequency.

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Leading-edge receptivity of a hypersonic boundary layer on a flat plate

Cited by 140 publications

References 20 publications

Numerical Simulation and Theoretical Analysis of Perturbations in Hypersonic Boundary Layers

Numerical Simulation and Theoretical Analysis of Perturbations in Hypersonic Boundary Layers

Response and receptivity of the hypersonic boundary layer past a wedge to free-stream acoustic, vortical and entropy disturbances

Numerical simulation of the supersonic boundary layer interaction with arbitrary oriented acoustic waves

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