Experimental investigation of the stability of a supersonic boundary layer on a plate with blunting of the leading edge

Lebiga, V. A.; Маслов, А. А.; Pridanov, V. G.

doi:10.1007/bf01089672

Cited by 9 publications

(8 citation statements)

References 6 publications

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“…For values of the X coordinate corresponding to the maxima 1--5 the Mach number between the plates depends mainly on the distance [11]. Curve 2 corresponds to the lower branch of the neutral stability curve, and curve 5 to the acoustic branch (maximum amplification of the acoustic perturbations by the laminar supersonic boundary layer).…”

Section: Introductionmentioning

confidence: 99%

Excitation of natural oscillations in a boundary layer by an external acoustic field

Маслов¹,

Semenov²

1986

Fluid Dyn

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which is perfectly possible in practice), since in a separate numerical solution of system (4.2) as a result of the errors it is also possible to obtain several different limiting values of v as r ~ 0. LITERATURE CITED1. L. Lees, "Laminar heat transfer over blunt-nosed bodies at hypersonic flight speeds," Jet Propul., 26, 259 (1956). 2. V. S. Avduevskii, B. M. Galitseiskii, G. A. Glebov, et al., Fundamentals of Heat Transfer in Aerospace Technology [in Russian], Mashinostroenie, Moscow (1975), Chaps. ll, 12, 15. 3. J. V. Rakich and G. G. Mateer, "Calculation of metric coefficients for streamline coordinates," AIAA J., l__q0, 1538(1972). 4. V. V. Lunev, Hypersonic Aerodynamics [in Russian], Nashinostroenie, Moscow (1975. 5. R. A. Safiullin, "Heat transfer in the laminar-turbulent boundary layer transition zone," Izv.

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Section: Introductionmentioning

confidence: 99%

Excitation of natural oscillations in a boundary layer by an external acoustic field

Маслов¹,

Semenov²

1986

Fluid Dyn

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“…Possibility of its prediction depends on the amplitude of an external sound wave. In experiments [11] integrated amplitude didn't exceed 4%. The amplitude ten times less i.e.…”

Section: Aeroacoustics Of Supersonic Boundary Layersmentioning

confidence: 78%

“…Mostly hot wire probe reacts to mass flux pulsations. A detailed description of the experiment is given in [11].…”

Section: Figurementioning

confidence: 99%

“…The problem on the excitation of unstable waves by sound was considered by Gaponov [9]. Gaponov et al [10], Lebiga et al [11] studied the interaction of sound with a supersonic boundary layer experimentally where the main results of Gaponov [8] theory were confirmed. Using a controlled acoustic field Maslov and Semionov [12] have shown that the boundary layer receptivity to the acoustic disturbances depends on the location of the interaction region.…”

Section: Introductionmentioning

confidence: 99%

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Aeroacoustics of Supersonic Boundary Layers

Гапонов

2014

International Journal of Aeroacoustics

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Present paper is devoted to those acoustical problems which are also related to the problem of the turbulence onset in high-speed boundary layers. Basic equations governing linear development of both hydrodynamic and acoustic waves in high-speed boundary layers are presented. Results of the theoretical investigation on external acoustic wave influence on the flat plate boundary layer are described. The intensity of disturbances excited by an acoustic wave inside the boundary layer has been studied. It has been found that interaction of sound with the boundary layer lead to an increase of the amplitude of disturbances inside the boundary. It has been shown that the amplitude of fluctuations inside the boundary layer may exceed the amplitude of the external acoustic field in many times. Besides in the paper nonlinear generation of increasing perturbations by acoustics is studied.

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“…If the issues of stability of the laminar boundary layer at subsonic speeds were studied thoroughly in both experimental and theoretical papers [1,2], for supersonic speeds these problems are less investigated [1,[3][4][5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

Panina

Kosinov

Семёнов

et al. 2017

AIP Conference Proceedings

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Abstract.The results of an experimental study of the controlled pulsations development in the spanwise modulated boundary layer of a swept wing are presented in the paper. The experiments were conducted at Mach 2 and unit Reynolds number Re1 = 6×10 6 m -1 . The square stickers were applied to induce the spanwise modulation of mean flow in the boundary layer. It was obtained, that the presence of roughness leads to a decrease of the disturbance source efficiency at the subharmonic and fundamental frequency, and the oblique breakdown mechanism begins to appear at smaller values of the longitudinal coordinate x as compared with the case of a smooth wing.

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Experimental investigation of the stability of a supersonic boundary layer on a plate with blunting of the leading edge

Cited by 9 publications

References 6 publications

Excitation of natural oscillations in a boundary layer by an external acoustic field

Excitation of natural oscillations in a boundary layer by an external acoustic field

Aeroacoustics of Supersonic Boundary Layers

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

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