Experimental Research of Adiabatic Wall Temperature Influenced by Separated Supersonic Flow

Попович, С. С.; Kirill, Egorov; Vinogradov, Urii A.

doi:10.1615/ihtc15.fcv.008962

Cited by 5 publications

(2 citation statements)

References 27 publications

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“…Максимальное значение коэффициент восстановления температуры достигает в области присоединения пограничного слоя -в районе 2 x H  . Данный результат соответствует результатам ранее проведенного исследования по влиянию падающего скачка уплотнения на адиабатную температуру стенки [29,30]. При этом ниже по течению наблюдается снижение коэффициента восстановления температуры на всей длине модели на расстоянии до 20 калибров ниже по течению за уступом.…”

Section: рис 6 график изменения теплового потока на стенке модели вunclassified

Aerodynamic cooling for supersonic wake flow behind a backward-facing step

Попович¹

2019

PhChGD

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The results of an experimental study of the effect of reducing the adiabatic wall temperature (aerodynamic cooling) for a case of separated supersonic flow behind a backward-facing ledge are presented. The study was conducted on unsteady-state regime during the launching a wind tunnel before reaching the equilibrium thermal state. The parameters of thermal gas dynamics were compared with the results obtained for the case of continuous flow around the smooth wall. The free-stream Mach number was 2.2, the Reynolds number along the length of the dynamic boundary layer was at least 20 million at the nozzle exit section. The height of the step ranged from 8 to 12 mm. The graphs of the wall temperature, stagnation flow temperature, adiabatic wall temperature, the total and static pressure, the heat flux, the distribution of the temperature recovery coefficient and the relative Stanton number along the length of the model are presented. The studies were carried out in the joint inter-university laboratory of MSU-BMSTU "Thermal Gas Dynamics" on the experimental base of the

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Section: рис 6 график изменения теплового потока на стенке модели вunclassified

Aerodynamic cooling for supersonic wake flow behind a backward-facing step

Попович¹

2019

PhChGD

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“…Experiments have been conducted in supersonic wind tunnel during its launching [12,13]. Flow velocity in the working area was changed with the use of plane variable supersonic nozzle in range of Mach numbers 2.0÷3.0.…”

Section: Experimental Apparatus Instrumentation and Techniquementioning

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Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow

et al. 2017

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Abstract. Investigations of supersonic air flow around plane surface behind a rib perpendicular to the flow direction are performed. Research was carried out for free stream Mach number 2.25 and turbulent flow regime -Rex>2·10 7 . Rib height was varied in range from 2 to 8 mm while boundary layer thickness at the nozzle exit section was about 6 mm. As a result adiabatic wall temperature and heat transfer coefficient are obtained for flow around plane surface behind a rib in contrast with the flow around plane surface without any disturbances.

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Indoor shockwave propagation modeling in a closed space

Firsova¹,

Taranov²

2019

Second International Conference on Material Science, Smart Structures and Applications: Icmss-2019

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Experimental Research of Adiabatic Wall Temperature Influenced by Separated Supersonic Flow

Cited by 5 publications

References 27 publications

Aerodynamic cooling for supersonic wake flow behind a backward-facing step

Aerodynamic cooling for supersonic wake flow behind a backward-facing step

Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow

Indoor shockwave propagation modeling in a closed space

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