Pressure loss reduction of a radial supersonic internal flow

Kazumi Tsunoda, Masayuki Ono, Toshiaki Asai

Research output: Contribution to journalArticle

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.

Original languageEnglish
Pages (from-to)3205-3212
Number of pages8
JournalNihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B
Volume64
Issue number626
Publication statusPublished - 1998 Oct
Externally publishedYes

Fingerprint

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

Keywords

  • Internal flow
  • Pressure loss
  • Radial flow
  • Riblet
  • Shock wave
  • Stagnation pressure
  • Supersonic flow

ASJC Scopus subject areas

  • Mechanical Engineering
  • Condensed Matter Physics

Cite this

Pressure loss reduction of a radial supersonic internal flow. / Tsunoda, Kazumi; Ono, Masayuki; Asai, Toshiaki.

In: Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, Vol. 64, No. 626, 10.1998, p. 3205-3212.

Research output: Contribution to journalArticle

@article{ecae9b6578524ebb93915ae621e436f2,
title = "Pressure loss reduction of a radial supersonic internal flow",
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.",
keywords = "Internal flow, Pressure loss, Radial flow, Riblet, Shock wave, Stagnation pressure, Supersonic flow",
author = "Kazumi Tsunoda and Masayuki Ono and Toshiaki Asai",
year = "1998",
month = "10",
language = "English",
volume = "64",
pages = "3205--3212",
journal = "Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B",
issn = "0387-5016",
publisher = "Japan Society of Mechanical Engineers",
number = "626",

}

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

UR - http://www.scopus.com/inward/record.url?scp=71249134638&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=71249134638&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:71249134638

VL - 64

SP - 3205

EP - 3212

JO - Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B

JF - Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B

SN - 0387-5016

IS - 626

ER -