Hypersonic Short-Duration Facilities for Aerodynamic Research at ITAM, Russia

Фомин, В. М.; Kharitonov, A. M.; Маслов, А. А.; Shiplyuk, A. N.; Yaroslavtsev, M. I.; Звегинцев, В. И.

doi:10.1007/978-3-319-23745-9_10

Cited by 11 publications

(1 citation statement)

References 10 publications

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“…The experiments were carried out in the wind tunnel "Transit-M" of ITAM SB RAS [8] with the Mach number M = 5.95, the stagnation temperature 0 = 360 418 K and the stagnation pressure P 0 = 3.7 46,1 atm. The unit Reynolds number varied in the range Re 1 = (4.5÷65.5) 10 6 1/m.…”

Section: Experimental Equipmentmentioning

confidence: 99%

The effect of roughness of blunted nose of cone on the development of disturbances and laminar-turbulent transition in a hypersonic boundary layer

Gromyko

Bountin

Polivanov

et al. 2017

AIP Conference Proceedings

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Abstract. The paper presents data on the effect of a distributed roughness of the blunted nose of the cone on the position of the laminar-turbulent transition. The studies were carried out at Mach number 5.95. It is found that the position of the roughness plays an important role in the transition process, it is obtained that the roughness has the greatest effect on the t the presence of a roughness on the nose of the model, even at subcritical Reynolds numbers, affects the pulsation processes in the boundary layer.

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Section: Experimental Equipmentmentioning

confidence: 99%

The effect of roughness of blunted nose of cone on the development of disturbances and laminar-turbulent transition in a hypersonic boundary layer

Gromyko

Bountin

Polivanov

et al. 2017

AIP Conference Proceedings

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Analysis of disturbances in a hypersonic boundary layer on a cone with heating/cooling of the nose tip

2018

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Experimental results of the influence of local heating/cooling on the development of hypersonic boundary layer disturbances are reported. Local heating/cooling is applied at the cone nose tip. The experiments are carried out at the Mach number M = 5.95, stagnation temperature T0 = 360–418 K, and stagnation pressure P0 = 3.7–45 atm. The unit Reynolds number is varied in the interval Re1 = (4.5–63) × 106 m−1. The investigations are conducted in the boundary layer on a cone with an apex half-angle of 7° and varied bluntness radius of the nose tip [R = 0.03 (sharp nose), 0.75, and 1.5 mm] for different values of the local temperature factor. The nose tip is heated by an ohmic heater. Cooling is performed by supplying liquid nitrogen into the internal cavity of the model nose. A comparative analysis of pressure pulsation spectra on the cone surface is performed. It is demonstrated that heating/cooling in the case of a sharp cone leads to flow destabilization/stabilization. The opposite effect is observed for blunted cones: heating/cooling stabilizes/destabilizes the second-mode disturbances. This effect is enhanced by increasing the nose tip bluntness. All the observed effects vanish with distance downstream from the nose tip.

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Influence of surface sublimation on the stability of the supersonic boundary layer and the laminar–turbulent transition

et al. 2021

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We report a theoretical study of the properties of a supersonic boundary layer and its linear stability under conditions of surface material sublimation. Calculations were performed for an adiabatic boundary layer for a flat plate with a naphthalene coating at a free-stream Mach number of M = 3 (for the first instability mode disturbances). In the boundary layer, surface sublimation generates a binary mixture flow (air and foreign vapors). This flow is studied using local self-similar boundary layer equations, and it is shown that the rise in the flow stagnation temperature and the corresponding evaporation of the wall material cause significant wall cooling and an increase in the near-wall density of the binary mixture. This modification of the boundary layer profiles leads to a decrease in the disturbance amplification rates. This is confirmed by calculations based on linear stability theory (LST). Boundary-layer stabilization occurs with an increase in stagnation temperature. The influence of surface sublimation on the position of the laminar–turbulent transition was estimated by means of the LST-based eN method. The possibility of increasing the transition Reynolds number by application of the sublimation coating is demonstrated. The results of pilot boundary layer transition experiments performed in a hot-shot wind tunnel are reported. For the first time, a delay in the transition due to the application of a naphthalene coating was experimentally demonstrated. It is also shown that surface sublimation leads to an increase in the growth rates of the second and third instability modes for a Mach 8 boundary layer.

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Hypersonic Short-Duration Facilities for Aerodynamic Research at ITAM, Russia

Cited by 11 publications

References 10 publications

The effect of roughness of blunted nose of cone on the development of disturbances and laminar-turbulent transition in a hypersonic boundary layer

The effect of roughness of blunted nose of cone on the development of disturbances and laminar-turbulent transition in a hypersonic boundary layer

Analysis of disturbances in a hypersonic boundary layer on a cone with heating/cooling of the nose tip

Influence of surface sublimation on the stability of the supersonic boundary layer and the laminar–turbulent transition

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