中国科学院力学研究所机构知识库
Advanced  
IMECH-IR  > 高温气体动力学国家重点实验室  > 期刊论文
Title:
基于实验设计方法的高超声速飞机前缘型线优化分析
Alternative Title: OPTIMIZATION AND ANALYSIS OF THE LEADING EDGE SHAPE FOR HYPERSONIC AIRPLANES BASED ON DOE METHODS1)
Author: 胡守超; 崔凯; 李广利; 肖尧; 司徒明
Source: 力学学报
Issued Date: 2016
Volume: 48, Issue:2, Pages:290-299
Abstract: 为探索前缘线变化对吸气式高超声速飞机气动性能的影响,基于一种旁侧进气布局翼身融合体构型,在飞行马赫数6,攻角4ffi和高度26 km的巡航飞行条件下,结合运用增量修正参数化设计方法、均匀实验设计方法和计算流体力学模拟,分析了飞行器前缘型线与其升阻力系数及纵向压心等性能参数间的关系.计算结果表明,前缘线形状对飞行器升阻力系数明显高于其对纵向压心影响,设计空间范围内升力系数变化约21.3%,阻力系数变化约31.8%,升阻比变化范围约10.63%,但相对压心变化范围仅为3.87%.在此基础上,通过对典型构型物面压力分布进行分析,发现前缘线形状适当弯曲可利用飞行器下表面侧壁压缩产生的高压气流,利用二者的耦合效应使飞行器获得额外的升力增量.
English Abstract: By taking a Blend-Wing-Body configuration with dual flanking inlets layout as the baseline, an aerodynamic shape optimization study for the leading edge of the vehicle is carried out. An increment-based method is developed to parameterize the leading edge, and the uniform design method is taken as the optimization driver. Totally 31 configurations with different leading edge shapes are generated, and then the aerodynamic performance of all configurations are evaluated by computational fluid dynamic simulation in the cruising conditions of Mach 6, flight altitude 26 km, and flight angle of attack 4ffi. Numerical results show that the relative variations of the lift and the drag coefficients in whole design space are 21.3% and 31.8%, respectively. Consequently, the relative variation of the lift-to-drag ratio is about 10.63%. In contrast, the maximal value of the relative position transition for the longitudinal pressure center is only 3.87%. Besides, the results also indicate that there is a proportional relationship between the vertical project area and the lift or drag coefficients. Finally, the effect of the leading edge deformation on the aerodynamic characteristics is analyzed on the basis of the results, and some primary rules are concluded. A concave shape of the leading edge is benefit to the improvement of the lift-to-drag ratio, while a convex one leads to a large lift coefficient.
Keyword: hypersonic airplane ; air-breathing vehicle ; shape optimization ; parameterization ; uniform design
Language: 中文
Indexed Type: EI ; CSCD
Correspondent Email: kcui@imech.ac.cn
DOC Type: 期刊论文
WOS Keyword Plus: hypersonic airplane ; air-breathing vehicle ; shape optimization ; parameterization ; uniform design
ISSN: 0459-1879
Funder: 国家自然科学基金资助项目
Rank: 胡守超, 中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京 100190, 中国.; 崔凯, 中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京 100190, 中国.; 李广利, 中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京 100190, 中国.; 肖尧, 中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京 100190, 中国.; 司徒明, 中国航天科工集团31研究所, 北京 100074, 中国.
CSCD ID: CSCD:5670483
Department: LHD气动布局优化与计算方法
Classification: 二类
First Institution (Yes or Not): True
Citation statistics:
Content Type: 期刊论文
URI: http://dspace.imech.ac.cn/handle/311007/59827
Appears in Collections:高温气体动力学国家重点实验室_期刊论文

Files in This Item: Download All
File Name/ File Size Content Type Version Access License
a2016-220.pdf(1239KB)期刊论文作者接受稿开放获取View Download

Recommended Citation:
胡守超,崔凯,李广利,等. 基于实验设计方法的高超声速飞机前缘型线优化分析[J]. 力学学报,2016-01-01,48(2):290-299.
Service
Recommend this item
Sava as my favorate item
Show this item's statistics
Export Endnote File
Google Scholar
Similar articles in Google Scholar
[胡守超]'s Articles
[崔凯]'s Articles
[李广利]'s Articles
CSDL cross search
Similar articles in CSDL Cross Search
[胡守超]‘s Articles
[崔凯]‘s Articles
[李广利]‘s Articles
Related Copyright Policies
Null
Social Bookmarking
Add to CiteULike Add to Connotea Add to Del.icio.us Add to Digg Add to Reddit
文件名: a2016-220.pdf
格式: Adobe PDF
所有评论 (0)
暂无评论
 
评注功能仅针对注册用户开放,请您登录
您对该条目有什么异议,请填写以下表单,管理员会尽快联系您。
内 容:
Email:  *
单位:
验证码:   刷新
您在IR的使用过程中有什么好的想法或者建议可以反馈给我们。
标 题:
 *
内 容:
Email:  *
验证码:   刷新

Items in IR are protected by copyright, with all rights reserved, unless otherwise indicated.

 

 

Valid XHTML 1.0!
Copyright © 2007-2017  中国科学院力学研究所 - Feedback
Powered by CSpace