Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions

Hidemasa Miyamoto, Akiko Matsuo, Takayuki Kojima, Hideyuki Taguchi

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

Numerical analyses of ideal contoured rectangular plug nozzle of DPR (design pressure ratio)=96 considering actual flight conditions were conducted to evaluate its performance. Drastic decreases in thrust efficiency coefficient were observed at transonic flight condition. The effect of intentionally setting the nozzle DPR low was also investigated, and it was found that using nozzle of DPR=19 in the same flight conditions, the transonic thrust efficiency decrease remarkably reduced compared to the DPR=96 nozzle. Furthermore, only 5% decrease in thrust efficiency occurred at cruising condition even though its nozzle size (exit area) is less than 1/3 of the DPR=96 nozzle. Researches were also made to seek for means to further improve the thrust performance during the transonic flight by modifying the nozzle's cowl geometry configuration. Here, thrust efficiency of the DPR=19 nozzle at transonic flight improved up to 2.6% by providing an extended cowl with a slit near the nozzle throat.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
Pages245-253
Number of pages9
Volume1
Publication statusPublished - 2007
Event45th AIAA Aerospace Sciences Meeting 2007 - Reno, NV, United States
Duration: 2007 Jan 82007 Jan 11

Other

Other45th AIAA Aerospace Sciences Meeting 2007
CountryUnited States
CityReno, NV
Period07/1/807/1/11

Fingerprint

plug nozzles
pressure ratio
nozzles
numerical analysis
Numerical analysis
Nozzles
transonic flight
thrust
geometry
flight conditions
flight
Geometry
nozzle design
nozzle geometry
transonic flow
throats
Nozzle design
slits
analysis
coefficients

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Miyamoto, H., Matsuo, A., Kojima, T., & Taguchi, H. (2007). Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions. In Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting (Vol. 1, pp. 245-253)

Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions. / Miyamoto, Hidemasa; Matsuo, Akiko; Kojima, Takayuki; Taguchi, Hideyuki.

Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting. Vol. 1 2007. p. 245-253.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Miyamoto, H, Matsuo, A, Kojima, T & Taguchi, H 2007, Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions. in Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting. vol. 1, pp. 245-253, 45th AIAA Aerospace Sciences Meeting 2007, Reno, NV, United States, 07/1/8.
Miyamoto H, Matsuo A, Kojima T, Taguchi H. Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions. In Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting. Vol. 1. 2007. p. 245-253
Miyamoto, Hidemasa ; Matsuo, Akiko ; Kojima, Takayuki ; Taguchi, Hideyuki. / Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions. Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting. Vol. 1 2007. pp. 245-253
@inproceedings{856f04704078470591b736c1509b3747,
title = "Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions",
abstract = "Numerical analyses of ideal contoured rectangular plug nozzle of DPR (design pressure ratio)=96 considering actual flight conditions were conducted to evaluate its performance. Drastic decreases in thrust efficiency coefficient were observed at transonic flight condition. The effect of intentionally setting the nozzle DPR low was also investigated, and it was found that using nozzle of DPR=19 in the same flight conditions, the transonic thrust efficiency decrease remarkably reduced compared to the DPR=96 nozzle. Furthermore, only 5{\%} decrease in thrust efficiency occurred at cruising condition even though its nozzle size (exit area) is less than 1/3 of the DPR=96 nozzle. Researches were also made to seek for means to further improve the thrust performance during the transonic flight by modifying the nozzle's cowl geometry configuration. Here, thrust efficiency of the DPR=19 nozzle at transonic flight improved up to 2.6{\%} by providing an extended cowl with a slit near the nozzle throat.",
author = "Hidemasa Miyamoto and Akiko Matsuo and Takayuki Kojima and Hideyuki Taguchi",
year = "2007",
language = "English",
isbn = "1563478900",
volume = "1",
pages = "245--253",
booktitle = "Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting",

}

TY - GEN

T1 - Numerical analysis of rectangular plug nozzle considering practical geometry and flow conditions

AU - Miyamoto, Hidemasa

AU - Matsuo, Akiko

AU - Kojima, Takayuki

AU - Taguchi, Hideyuki

PY - 2007

Y1 - 2007

N2 - Numerical analyses of ideal contoured rectangular plug nozzle of DPR (design pressure ratio)=96 considering actual flight conditions were conducted to evaluate its performance. Drastic decreases in thrust efficiency coefficient were observed at transonic flight condition. The effect of intentionally setting the nozzle DPR low was also investigated, and it was found that using nozzle of DPR=19 in the same flight conditions, the transonic thrust efficiency decrease remarkably reduced compared to the DPR=96 nozzle. Furthermore, only 5% decrease in thrust efficiency occurred at cruising condition even though its nozzle size (exit area) is less than 1/3 of the DPR=96 nozzle. Researches were also made to seek for means to further improve the thrust performance during the transonic flight by modifying the nozzle's cowl geometry configuration. Here, thrust efficiency of the DPR=19 nozzle at transonic flight improved up to 2.6% by providing an extended cowl with a slit near the nozzle throat.

AB - Numerical analyses of ideal contoured rectangular plug nozzle of DPR (design pressure ratio)=96 considering actual flight conditions were conducted to evaluate its performance. Drastic decreases in thrust efficiency coefficient were observed at transonic flight condition. The effect of intentionally setting the nozzle DPR low was also investigated, and it was found that using nozzle of DPR=19 in the same flight conditions, the transonic thrust efficiency decrease remarkably reduced compared to the DPR=96 nozzle. Furthermore, only 5% decrease in thrust efficiency occurred at cruising condition even though its nozzle size (exit area) is less than 1/3 of the DPR=96 nozzle. Researches were also made to seek for means to further improve the thrust performance during the transonic flight by modifying the nozzle's cowl geometry configuration. Here, thrust efficiency of the DPR=19 nozzle at transonic flight improved up to 2.6% by providing an extended cowl with a slit near the nozzle throat.

UR - http://www.scopus.com/inward/record.url?scp=34250875839&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34250875839&partnerID=8YFLogxK

M3 - Conference contribution

SN - 1563478900

SN - 9781563478901

VL - 1

SP - 245

EP - 253

BT - Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting

ER -