Experiment on fluidic thrust-vectoring nozzle based on shock control concept

Zhan Xue Wang; Yu Nan Wang; Zhi Jie Li; Xiao Long Xin

Experiment on fluidic thrust-vectoring nozzle based on shock control concept

Zhan Xue Wang
, Yu Nan Wang
, Zhi Jie Li
, Xiao Long Xin

School of Power and Energy

Research output: Contribution to journal › Article › peer-review

16 Scopus citations

Abstract

An experimental investigation for the aerodynamic effects of fluidic injection in a two-dimensional, convergent-divergent (2DCD) nozzle has been conducted. Simulations were performed at static conditions of a single fluidic injection port with variable injection angles (60°, 90° and 120°) at a relative position of x/x_l=0.688, with the scheduled nozzle pressure ratios (NPR, from 4.5 to 13.89) and secondary to primary total pressure ratios(SPR) from 0.4 to 1.0. Results indicated a pressure rise on the nozzle wall centerline. It validated that the nozzle thrust vectoring angle and thrust coefficient change with different NPRs, SPRs and injection angles.

Original language	English
Pages (from-to)	751-756
Number of pages	6
Journal	Tuijin Jishu/Journal of Propulsion Technology
Volume	31
Issue number	6
State	Published - Dec 2010

Keywords

Fluidic thrust vectoring
Shock vectoring control
Vector angle

Cite this

@article{13c50d2008b9480bae1e6e0215120c6d,

title = "Experiment on fluidic thrust-vectoring nozzle based on shock control concept",

abstract = "An experimental investigation for the aerodynamic effects of fluidic injection in a two-dimensional, convergent-divergent (2DCD) nozzle has been conducted. Simulations were performed at static conditions of a single fluidic injection port with variable injection angles (60°, 90° and 120°) at a relative position of x/xl=0.688, with the scheduled nozzle pressure ratios (NPR, from 4.5 to 13.89) and secondary to primary total pressure ratios(SPR) from 0.4 to 1.0. Results indicated a pressure rise on the nozzle wall centerline. It validated that the nozzle thrust vectoring angle and thrust coefficient change with different NPRs, SPRs and injection angles.",

keywords = "Fluidic thrust vectoring, Shock vectoring control, Vector angle",

author = "Wang, \{Zhan Xue\} and Wang, \{Yu Nan\} and Li, \{Zhi Jie\} and Xin, \{Xiao Long\}",

year = "2010",

month = dec,

language = "英语",

volume = "31",

pages = "751--756",

journal = "Tuijin Jishu/Journal of Propulsion Technology",

issn = "1001-4055",

publisher = "Journal of Propulsion Technology",

number = "6",

}

TY - JOUR

T1 - Experiment on fluidic thrust-vectoring nozzle based on shock control concept

AU - Wang, Zhan Xue

AU - Wang, Yu Nan

AU - Li, Zhi Jie

AU - Xin, Xiao Long

PY - 2010/12

Y1 - 2010/12

N2 - An experimental investigation for the aerodynamic effects of fluidic injection in a two-dimensional, convergent-divergent (2DCD) nozzle has been conducted. Simulations were performed at static conditions of a single fluidic injection port with variable injection angles (60°, 90° and 120°) at a relative position of x/xl=0.688, with the scheduled nozzle pressure ratios (NPR, from 4.5 to 13.89) and secondary to primary total pressure ratios(SPR) from 0.4 to 1.0. Results indicated a pressure rise on the nozzle wall centerline. It validated that the nozzle thrust vectoring angle and thrust coefficient change with different NPRs, SPRs and injection angles.

AB - An experimental investigation for the aerodynamic effects of fluidic injection in a two-dimensional, convergent-divergent (2DCD) nozzle has been conducted. Simulations were performed at static conditions of a single fluidic injection port with variable injection angles (60°, 90° and 120°) at a relative position of x/xl=0.688, with the scheduled nozzle pressure ratios (NPR, from 4.5 to 13.89) and secondary to primary total pressure ratios(SPR) from 0.4 to 1.0. Results indicated a pressure rise on the nozzle wall centerline. It validated that the nozzle thrust vectoring angle and thrust coefficient change with different NPRs, SPRs and injection angles.

KW - Fluidic thrust vectoring

KW - Shock vectoring control

KW - Vector angle

UR - https://www.scopus.com/pages/publications/79952471553

M3 - 文章

AN - SCOPUS:79952471553

SN - 1001-4055

VL - 31

SP - 751

EP - 756

JO - Tuijin Jishu/Journal of Propulsion Technology

JF - Tuijin Jishu/Journal of Propulsion Technology

IS - 6

ER -

Experiment on fluidic thrust-vectoring nozzle based on shock control concept

Abstract

Keywords

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