Pressure loss reduction of a radial supersonic internal flow

Kazumi Tsunoda, Masayuki Ono, Toshiaki Asai

研究成果: Article

抄録

Thi paper describes the experimental study of the radial supersonic flow behavior over the riblet surface mounted on the disk-shaped wall to reduce a pressure loss. The experiments have been performed in an indraft supersonic wind tunnel installed with disk-shaped channel at Mach numbers ranging from 1.8 to 3.3 just in front of a pressure rise. The static pressure rise in the pseudo-shock region observed in a channel with riblet surface became milder than that for the case of smooth surface, and significance of its difference was indicated by uncertainty analysis entimated at 95% coverage. The contours of stagnation pressure obtained by traversing a Pitot-tube showed that a higher stagnation pressure was maintained near the riblet surface compared with that for the smooth surface. Furthermore, it was found that the stagnation pressure loss reduced about 20% near the riblet surface at a Mach number of 2.5.

元の言語English
ページ(範囲)3205-3212
ページ数8
ジャーナルNihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B
64
発行部数626
出版物ステータスPublished - 1998 10
外部発表Yes

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internal flow
riblets
stagnation pressure
Mach number
pitot tubes
supersonic wind tunnels
Uncertainty analysis
static pressure
supersonic flow
Supersonic flow
Wind tunnels
shock

ASJC Scopus subject areas

  • Mechanical Engineering
  • Condensed Matter Physics

これを引用

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abstract = "Thi paper describes the experimental study of the radial supersonic flow behavior over the riblet surface mounted on the disk-shaped wall to reduce a pressure loss. The experiments have been performed in an indraft supersonic wind tunnel installed with disk-shaped channel at Mach numbers ranging from 1.8 to 3.3 just in front of a pressure rise. The static pressure rise in the pseudo-shock region observed in a channel with riblet surface became milder than that for the case of smooth surface, and significance of its difference was indicated by uncertainty analysis entimated at 95{\%} coverage. The contours of stagnation pressure obtained by traversing a Pitot-tube showed that a higher stagnation pressure was maintained near the riblet surface compared with that for the smooth surface. Furthermore, it was found that the stagnation pressure loss reduced about 20{\%} near the riblet surface at a Mach number of 2.5.",
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TY - JOUR

T1 - Pressure loss reduction of a radial supersonic internal flow

AU - Tsunoda, Kazumi

AU - Ono, Masayuki

AU - Asai, Toshiaki

PY - 1998/10

Y1 - 1998/10

N2 - Thi paper describes the experimental study of the radial supersonic flow behavior over the riblet surface mounted on the disk-shaped wall to reduce a pressure loss. The experiments have been performed in an indraft supersonic wind tunnel installed with disk-shaped channel at Mach numbers ranging from 1.8 to 3.3 just in front of a pressure rise. The static pressure rise in the pseudo-shock region observed in a channel with riblet surface became milder than that for the case of smooth surface, and significance of its difference was indicated by uncertainty analysis entimated at 95% coverage. The contours of stagnation pressure obtained by traversing a Pitot-tube showed that a higher stagnation pressure was maintained near the riblet surface compared with that for the smooth surface. Furthermore, it was found that the stagnation pressure loss reduced about 20% near the riblet surface at a Mach number of 2.5.

AB - Thi paper describes the experimental study of the radial supersonic flow behavior over the riblet surface mounted on the disk-shaped wall to reduce a pressure loss. The experiments have been performed in an indraft supersonic wind tunnel installed with disk-shaped channel at Mach numbers ranging from 1.8 to 3.3 just in front of a pressure rise. The static pressure rise in the pseudo-shock region observed in a channel with riblet surface became milder than that for the case of smooth surface, and significance of its difference was indicated by uncertainty analysis entimated at 95% coverage. The contours of stagnation pressure obtained by traversing a Pitot-tube showed that a higher stagnation pressure was maintained near the riblet surface compared with that for the smooth surface. Furthermore, it was found that the stagnation pressure loss reduced about 20% near the riblet surface at a Mach number of 2.5.

KW - Internal flow

KW - Pressure loss

KW - Radial flow

KW - Riblet

KW - Shock wave

KW - Stagnation pressure

KW - Supersonic flow

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