钝头旋成体背涡迎角效应的分区性态

Zhongyang Qi; Yankui Wang; Peng Cao

doi:10.13700/j.bh.1001-5965.2018.0798

钝头旋成体背涡迎角效应的分区性态

Translated title of the contribution: Zonal behavior of angle of attack effects on vortices over blunt-slender body

Zhongyang Qi
, Yankui Wang^*
, Peng Cao

^*Corresponding author for this work

School of Aeronautic Science and Engineering

State Key Laboratory of Aerodynamics
Beihang University
Shanghai Institute of Spaceflight Control Technology

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

2 Scopus citations

Abstract

In order to achieve the high maneuverability of the air-to-air missile, the flow characteristics of vortices over the blunt-slender body at different angles of attack were studied by wind tunnel forces and pressure test in this paper. The Reynolds number is set as Re_D=1.54×10⁵, based on oncoming free-stream velocity and the diameter of the blunt-slender body (D). The flow structures over the blunt-slender body were determined at different angles of attack according to the analysis of side forces, sectional pressure distribution and the variation histories of the sectional side force with time. Four regions about the angles of attack are divided, i.e., attached-flow region (α≤10°), symmetric-flow region (10°<α≤20°), steady asymmetric-flow region (20°<α≤50°) and unsteady asymmetric-flow region (α>50°). The flow characteristics of vortices over the blunt-slender body at different angles of attack were discussed in detail.

Translated title of the contribution	Zonal behavior of angle of attack effects on vortices over blunt-slender body
Original language	Chinese (Traditional)
Pages (from-to)	2134-2140
Number of pages	7
Journal	Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
Volume	44
Issue number	10
DOIs	https://doi.org/10.13700/j.bh.1001-5965.2018.0798
State	Published - 1 Oct 2018

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10.13700/j.bh.1001-5965.2018.0798

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title = "钝头旋成体背涡迎角效应的分区性态",

abstract = "In order to achieve the high maneuverability of the air-to-air missile, the flow characteristics of vortices over the blunt-slender body at different angles of attack were studied by wind tunnel forces and pressure test in this paper. The Reynolds number is set as ReD=1.54×105, based on oncoming free-stream velocity and the diameter of the blunt-slender body (D). The flow structures over the blunt-slender body were determined at different angles of attack according to the analysis of side forces, sectional pressure distribution and the variation histories of the sectional side force with time. Four regions about the angles of attack are divided, i.e., attached-flow region (α≤10°), symmetric-flow region (10°<α≤20°), steady asymmetric-flow region (20°<α≤50°) and unsteady asymmetric-flow region (α>50°). The flow characteristics of vortices over the blunt-slender body at different angles of attack were discussed in detail.",

keywords = "Angle of attack effects, Asymmetric flow, Blunt-slender body, High angle of attack aerodynamics, Vortex structure",

author = "Zhongyang Qi and Yankui Wang and Peng Cao",

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month = oct,

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doi = "10.13700/j.bh.1001-5965.2018.0798",

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T1 - 钝头旋成体背涡迎角效应的分区性态

AU - Qi, Zhongyang

AU - Wang, Yankui

AU - Cao, Peng

PY - 2018/10/1

Y1 - 2018/10/1

N2 - In order to achieve the high maneuverability of the air-to-air missile, the flow characteristics of vortices over the blunt-slender body at different angles of attack were studied by wind tunnel forces and pressure test in this paper. The Reynolds number is set as ReD=1.54×105, based on oncoming free-stream velocity and the diameter of the blunt-slender body (D). The flow structures over the blunt-slender body were determined at different angles of attack according to the analysis of side forces, sectional pressure distribution and the variation histories of the sectional side force with time. Four regions about the angles of attack are divided, i.e., attached-flow region (α≤10°), symmetric-flow region (10°<α≤20°), steady asymmetric-flow region (20°<α≤50°) and unsteady asymmetric-flow region (α>50°). The flow characteristics of vortices over the blunt-slender body at different angles of attack were discussed in detail.

AB - In order to achieve the high maneuverability of the air-to-air missile, the flow characteristics of vortices over the blunt-slender body at different angles of attack were studied by wind tunnel forces and pressure test in this paper. The Reynolds number is set as ReD=1.54×105, based on oncoming free-stream velocity and the diameter of the blunt-slender body (D). The flow structures over the blunt-slender body were determined at different angles of attack according to the analysis of side forces, sectional pressure distribution and the variation histories of the sectional side force with time. Four regions about the angles of attack are divided, i.e., attached-flow region (α≤10°), symmetric-flow region (10°<α≤20°), steady asymmetric-flow region (20°<α≤50°) and unsteady asymmetric-flow region (α>50°). The flow characteristics of vortices over the blunt-slender body at different angles of attack were discussed in detail.

KW - Angle of attack effects

KW - Asymmetric flow

KW - Blunt-slender body

KW - High angle of attack aerodynamics

KW - Vortex structure

UR - https://www.scopus.com/pages/publications/85056799777

U2 - 10.13700/j.bh.1001-5965.2018.0798

DO - 10.13700/j.bh.1001-5965.2018.0798

M3 - 文章

AN - SCOPUS:85056799777

SN - 1001-5965

VL - 44

SP - 2134

EP - 2140

JO - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

JF - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

IS - 10

ER -

钝头旋成体背涡迎角效应的分区性态

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