Temperature of a thermally-insulated permeable wall in a compressible flow

Leont'ev, A. I.; Лущик, В. Г.; Yakubenko, A. E.

doi:10.1134/s0015462808050141

Cited by 8 publications

(1 citation statement)

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“…This relation was experimentally proven for air in and around Pr=0.7. At the same time some researchers consider influence of recovery factor from Reynolds, Mach and Prandtl numbers, injection/suction into/from the boundary layer, shape and relief of streamlined surface [5][6][7][8][9][10][11]. These results show that recovery factor can significantly differ from the mentioned approximation.…”

Section: Introductionmentioning

confidence: 63%

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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Section: Introductionmentioning

confidence: 63%

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

et al. 2017

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Distinctive features of heat transfer on a permeable surface in a laminar compressible gas flow at Prandtl number Pr < 1

Leontiev

Лущик

Макарова

2020

International Journal of Heat and Mass Transfer

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Experimental investigation of the temperature stratification of an air flow through a supersonic channel with a central body in the form of a porous permeable tube

Vinogradov¹,

Zditovets²,

Стронгин³

2013

Fluid Dyn

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Temperature of a thermally-insulated permeable wall in a compressible flow

Cited by 8 publications

References 5 publications

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

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

Distinctive features of heat transfer on a permeable surface in a laminar compressible gas flow at Prandtl number Pr < 1

Experimental investigation of the temperature stratification of an air flow through a supersonic channel with a central body in the form of a porous permeable tube

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Temperature of a thermally-insulated permeable wall in a compressible flow

Cited by 8 publications

References 5 publications

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

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

Distinctive features of heat transfer on a permeable surface in a laminar compressible gas flow at Prandtl number Pr < 1

Experimental investigation of the temperature stratification of an air flow through a supersonic channel with a central body in the form of a porous permeable tube

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Distinctive features of heat transfer on a permeable surface in a laminar compressible gas flow at Prandtl number Pr < 1