Computational Investigation of Overall Aerodynamic Characteristics for Spanwise Adaptive Wing

doi:10.7652/xjtuxb202010022

您当前的位置：

首页 >

文章列表页 >

Computational Investigation of Overall Aerodynamic Characteristics for Spanwise Adaptive Wing

更新时间：2025-07-09

- Computational Investigation of Overall Aerodynamic Characteristics for Spanwise Adaptive Wing
- Vol. 54, Issue 10, Pages: 174-184(2020)
- 作者机构：
  
  西安航空学院飞行器学院,西安,710077
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202010022
  CLC： V211.4
- Online First：10 October 2020，
  
  Published：2020
- 稿件说明：
移动端阅览
Computational Investigation of Overall Aerodynamic Characteristics for Spanwise Adaptive Wing[J]. 2020, 54(10): 174-184.
DOI：

Computational Investigation of Overall Aerodynamic Characteristics for Spanwise Adaptive Wing[J]. 2020, 54(10): 174-184. DOI： 10.7652/xjtuxb202010022.

摘要

针对展向自适应机翼的气动特性随折叠角度变化的问题

以经典翼型NACA0012为基础

设计了内外段比例为7:1的展向自适应机翼。基于结构化网格和雷诺平均N-S方程

采用自主开发的流场求解器

研究了自适应机翼在不同速域、不同折叠角度情况下的总体气动性能以及操纵特性。从升阻比和机翼表面压力分布两个方面

对比了外段机翼在不同折叠角度下的总体气动效率以及折叠角度对流场特性的影响规律。研究结果表明

自适应机翼的对称变形在合适的折叠角度下可以使亚声速和超声速飞行条件下的气动效率大幅增加

增幅高达28%; 亚声速飞行时的高气动效率来源于升力增加和阻力减小的共同作用

而超声速时的高气动效率主要来源于阻力的减小; 在跨声速飞行条件下的气动特性随折叠角度变化不明显; 非对称变形可以产生明显的用于方向操纵的滚转力矩和偏航力矩。通过将外段机翼折叠到不同角度

展向自适应机翼可以适应不同的飞行工况

获得更好的气动效益

可应用于下一代亚声速或超声速飞机。

Abstract

To determine the effect of folding angle on aerodynamic characteristics of spanwise adaptive wing

configuration with a 7:1 ratio between internal and external segments based on classical airfoil NACA0012 was designed. According to the structured grid and Reynolds averaged Navier-Stokes equations

the codes developed by ourselves were employed to investigate the overall aerodynamic performance and maneuverability in various speed domains and at different folding angles. The overall aerodynamic efficiency and folding angle effect on flow field characteristics at different folding angles of external wing were compared in terms of the lift-to-drag ratio and the wing surface pressure distribution. It is found that the symmetric folding of the spanwise adaptive wing can increase the aerodynamic efficiency significantly at appropriate folding angle in subsonic and supersonic flight regimes by up to 28%; the high aerodynamic efficiency in subsonic flight results from the combination of lift e

关键词

Keywords

references

张聚恩. 大国航空: 从百年奋发到世纪辉煌 [M]. 北京: 科学出版社, 2018: 151-172.

VALASEK J. Morphing aerospace vehicles and structures [M]. New York, USA: John Wiley Sons Ltd., 2013: 1-10.

CONCILIO A, DIMINO I, LECCE L, et al. Morphing wing technologies: large commercial aircraft and civil helicopters [M]. Amsterdam, Holland: Elsevier, 2017: 126-143.

LI Daochun, ZHAO Shiwei, DA RONCH A. A review of modelling and analysis of morphing wings [J]. Progress in Aerospace Sciences, 2018, 100: 46-62.

STANEWSKY E. Adaptive wing and flow control technology [J]. Progress in Aerospace Sciences, 2001, 37(7): 583-667.

BARBARINO S, BILGEN O, AJAJ R M. A review of morphing aircraft [J]. Journal of Intelligent Material Systems and Structures, 2011, 22(9): 823-877.

STANEWSKY E. Aerodynamic benefits of adaptive wing technology [J]. Aerospace Science and Technology, 2000, 4(7): 439-452.

ÖZGEN S, YAMAN Y, SAHIN M, et al. Morphing air vehicle concepts [EB/OL]. [2020-01-20]. https:∥www.researchgate.net/publication/228889328.

RODRIGUEZ A. Morphing aircraft technology survey [C]∥The 45th AIAA Aerospace Sciences Meeting and Exhibit. New York, USA: AIAA, 2007: 1258.

GOMEZ J C, GARCIA E. Morphing unmanned aerial vehicles [J]. Smart Materials and Structures, 2011, 20(10): 103001.

MOHOLT M, BENAFAN O. Spanwise adaptive wing [EB/OL]. [2020-02-02]. https: ∥ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20170009544.pdf.

LÓPEZ I. Convergent aeronautics solutions(CAS)project overview [EB/OL]. [2020-02-02]. https: ∥ntrs. nasa.gov/archive/nasa/casi.ntrs.nasa.gov/201700069 09.pdf.

THILL C, ETCHES J, BOND I, et al. Morphing skins [J]. The Aeronautical Journal, 2008, 112(1129): 117-139.

HENRY J, PINES D. A mathematical model for roll dynamics by use of a morphing-span wing [C]∥The 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. New York, USA: AIAA, 2007: 1708.

ZHANG Qing, HUA Ruhao, YE Zhengyin. Experi-mental and computational investigation of novel vertical tail buffet suppression method for high sweep delta wing [J]. Science China: Technological Sciences, 2015, 58(1): 147-157.

ZHANG Qing, YE Zhengyin. Novel method based on inflatable bump for vertical tail buffeting suppression [J]. Journal of Aircraft, 2015, 52(1): 367-371.

张庆, 叶正寅. 一种基于充气气囊的垂尾抖振抑制新方法研究 [J]. 工程力学, 2014, 31(12): 234-240.

ZHANG Qing, YE Zhengyin. Study on a new method for suppression of vertical tail buffeting using inflatable bumps [J]. Engineering Mechanics, 2014, 31(12): 234-240.

张庆. 高速再入飞行器动力学问题研究 [D]. 西安: 西北工业大学, 2018: 17-34.

华如豪, 叶正寅. 排式充气机翼的高效气动布局研究 [J]. 空气动力学学报, 2012, 30(2): 184-191.

HUA Ruhao, YE Zhengyin. Research on effective aerodynamic configuration of row inflatable wings [J]. Acta Aerodynamica Sinica, 2012, 30(2): 184-191.

张庆, 叶正寅. 排式双翼布局低雷诺数气动特性计算研究 [J]. 工程力学, 2019, 36(10): 244-256.

ZHANG Qing, YE Zhengyin. Computational investigations for aerodynamic characteristic analysis of low Reynolds number doubly-tandem wing configurations [J]. Engineering Mechanics, 2019, 36(10): 244-256.

杨磊. 空中发射分离过程的动力学问题研究 [D]. 西安: 西北工业大学, 2018: 21-30.

ZHANG Qing, YE Kun, YE Zhengyin, et al. Aerodynamic optimization for hypersonic wing design based on local piston theory [J]. Journal of Aircraft, 2016, 53(4): 1065-1072.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical Analysis of Lift Enhancement and Drag Reduction by Self-Induced Vibration of Localized Elastic Airfoil

Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade

Knowledge Graph Representation Learning Driven by Semantic Discrimination and Subgraph Integration

Effects of Expansion Angle Crater Film Hole on the Film Cooling Characteristics of a Double-Wall Structure

Sensitivity Analysis of Foil Geometrical Parameters for the Third-Generation CO2 Gas Foil Bearings Based on Design of Experiments Method

Related Author

康伟

张家忠

JIA Zhe

LI Feng

ZHANG Weixin

LIU Zhao

SHI Yan

FENG Zhenping

Related Institution

School of Energy and Power Engineering, Xi'an Jiaotong University

⁰