Direct numerical simulation of disturbances generated by periodic suction-blowing in a hypersonic boundary layer

Progress in Flight Physics

Ezhov

et al. 2017

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The §ow pattern and the heat §ux to a body surface at a tangential gas injecting have been investigated. The cooling air was injected to a §ow through the tangential axisymmetric slot on the spherically blunted cylinder. The experiments were conducted at M ∞ = 6, Re ∞,Rw = 0.76 · 10 6 , angle of attack α = 0 • 30 • , and the slot width h k /R w = 0 0.021. The mass rate of the injecting gas was G * = g j /(πρ ∞ u 2 ∞w ) = 0 0.16. It has been shown that maximum of the heat §ux toward the sphere surface can be su©ciently decreased. Numerical investigations have been carried out using the solution of the Navier Stokes equations for axisymmetric two-dimensional (2D) viscous compressible unsteady §ows at α = 0.

Section: Numerical Problem Formulation and Solution Methodsmentioning

confidence: 99%

Tangential injection to a supersonic flow on a blunted nose

Chuvakhov

Progress in Flight Physics

Ezhov

et al. 2017

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“…Hereinafter, asterisks denote dimensional variables. The §uid is a perfect gas with the speci¦c heat ratio γ = Details on the problem formulation and the governing equations are given in [10]. The computational domain is a rectangle with its bottom side corresponding to the cone surface for the region 0 ≤ x ≤ 1.…”

Section: Problem Formulationmentioning

confidence: 99%

“…The temperature distribution is smoothed near the boundaries in accord with the experimental measurements of T * w (x * ). The problem is solved numerically using the implicit second-order ¦nite-volume method described in [10]. The 2D (axisymmetric) Navier Stokes equations are approximated by a shock-capturing scheme that allows for modeling of §ow nonuniformities in the temperature jump vicinity.…”

Section: Problem Formulationmentioning

confidence: 99%

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Stability of high-speed boundary layer on a sharp cone with localized wall heating or cooling

Soudakov

Федоров

Progress in Flight Physics – Volume 7

2015

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A localized heating or cooling e¨ect on stability and transition of the boundary layer §ow on a sharp cone is analyzed at the Mach number 6. The mean §ows are calculated using axisymmetric Navier Stokes equations. The spatial linear stability analysis is performed for twodimensional (2D) disturbances related to the Mack second mode. The transition onset points are estimated using the e N method. In this framework, the heater or cooler may cause earlier or later transition depending on the choice of critical N -factor. Direct numerical simulations (DNS) of 2D wave propagating in the boundary layer are compared with stability results.

“…On in §ow and upper boundaries, conditions correspond to an undisturbed free stream. Details on the problem formulation and governing equations are given in [8].…”

Section: Numerical Simulationmentioning

confidence: 99%

Peculiarities of flow and heat transfer in the base region of generic model of martian descent vehicle

Borovoy

Progress in Flight Physics

Иванов

et al. 2012

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Some results concerning experimental and numerical investigations of Generic model of Martian descent vehicle (TC3 con¦guration) are presented. These investigations include determination of heat §ux and pressure on the all model surfaces at di¨erent angles of attack. Experiments were carried out in TsAGI£s wind tunnels UT-1 in air and in IT-2 in carbon dioxide. With the help of total pressure measurements, §ow in the model base region has been diagnosed at laminar and turbulent cases. The study is focused on heating of the base surface.