Receptivity of a hypersonic boundary layer over a flat plate with a porous coating

Егоров, И. В.; Федоров, А. В.; Soudakov, Vitaly

doi:10.1017/s0022112008000669

Cited by 97 publications

(40 citation statements)

References 35 publications

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“…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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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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“…For each case the laminar basic flow is computed using the in-house Navier-Stokes code HSFlow, and stability analyses are performed in the framework of linear stability theory (LST) using the in-house LST code. These tools were successfully exploited for stability and receptivity studies of high-speed boundary-layer flows [9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Theoretical-Numerical Analysis of Boundary-Layer Stability with Combined Injection and Acoustic Absorptive Coating

Федоров¹,

Soudakov²

2014

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)24 January 2014 REPORT TYPE Final Report PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)Moscow Institute of Physics and Technology 9, Institutskii per. Dolgoprudny, Moscow Region, 141700 Russia PERFORMING ORGANIZATION REPORT NUMBERN/A SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)Oleksiy SPONSOR/MONITOR'S ACRONYM(S)AFRL/AFOSR/IOE (EOARD) SPONSOR/MONITOR'S REPORT NUMBER(S) AFRL-AFOSR-UK-TR-2014-000112. DISTRIBUTION/AVAILABILITY STATEMENT Distribution A: Approved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThis report summarizes results of stability analyses performed for a slender sharp cone with and without injection of air through a porous strip. The free-stream parameters are related to the experiments in the Caltech's T5 shock tunnel. The analysis is focused on pure aerodynamic effects in the framework of perfect gas model. It was shown that the injection leads to destabilization of acoustic modes in the near-field relaxation region. To reduce this detrimental effect it was suggested to alter the injector surface shape or use suction-blowing of zero net injection. However, stability computations showed that these modifications did not improve the injector performance. The porous wall effect on the acoustic instability was also examined. It was found that porosity stabilizes the boundary layer flow with and without injection. This indicates that the injector performance can be improved, if the porous layer, which is used for the injection, is protruded downstream to cover the near-filed relaxation region. SUBJECT TERMSEOARD, Boundary Layer, BL absorption, BL stability, BL injuection, hyperconic BL 1 AbstractThis report summarizes results of stability analyses performed for a slender sharp cone with and without injection of air through a porous strip. The free-stream parameters are related to the experiments in the Caltech's T5 shock tunnel. The analysis is focused on pure aerodynamic effects in the framework of perfect gas model. It was shown that the injection leads to destabilization of acoustic modes in the near-field relaxation region. To reduce ...

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“…The VSL consists of a thick boundary layer and a thin layer of an inviscid §ow behind the SW. Like the boundary layer, the laminar shock layer is unstable, and perturbations developed in this layer induce its transition to the turbulent §ow regime. The evolution of perturbations in supersonic §ows with Mach numbers 6 and 10 was studied by Egorov et al [1,2] and Ma and Zhong [3,4]. However, mechanisms governing emergence and development of perturbations in the VSL with higher Mach numbers may di¨er from those investigations with lower Mach numbers.…”

Section: Introductionmentioning

confidence: 99%

Active control of hypersonic shock layer disturbances

Poplavskaya

Маслов

2012

Progress in Flight Physics

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This is a brief review of the investigations of receptivity and control of hypersonic shock layers. The present paper describes comprehensive numerical and experimental investigations of evolution of disturbances generated in the hypersonic viscous shock layer (VSL) on a §at plate by external acoustic waves and by perturbations introduced into the shock layer from the surface of model. The active control of intensity of pulsations is possible because both external acoustic waves and the periodic controlled disturbances introduced on the plate surface generate, in a shock layer, entropy-vorticity disturbances with identical spatial distributions and phase velocities.

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Receptivity of a hypersonic boundary layer over a flat plate with a porous coating

Cited by 97 publications

References 35 publications

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

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

Theoretical-Numerical Analysis of Boundary-Layer Stability with Combined Injection and Acoustic Absorptive Coating

Active control of hypersonic shock layer disturbances

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