空天飞行器机翼/翼型的需求分析及应用

罗金玲; 龙双丽; 汤继斌; 韩忠华; 张阳

doi:10.7638/kqdlxxb-2021.0237

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空天飞行器机翼/翼型的需求分析及应用

翼型研究新进展 | 更新时间：2026-05-28

- 空天飞行器机翼/翼型的需求分析及应用
- Requirement analyses and optimized design of wing/airfoil for aerospace vehicles
- 空气动力学学报 2021年39卷第6期页码：101-110
- 作者机构：
  
  1. 北京空天技术研究所,北京,100074
  2. 西北工业大学翼型、叶栅空气动力学国家级重点实验室,西安,710072
- 作者简介：
  
  罗金玲*（1964-），女，博士，研究员，主要研究方向：飞行器设计. E-mail：nuaalsl@qq.com
- 基金信息：
  
  装发快速支持项目（80906010101）
- DOI：10.7638/kqdlxxb-2021.0237
  中图分类号： V224
- 纸质出版：2021
- 稿件说明：
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罗金玲, 龙双丽, 汤继斌, 等. 空天飞行器机翼/翼型的需求分析及应用[J]. 空气动力学学报, 2021, 39(6): 101−110.

LUO Jinling, LONG Shuangli, TANG Jibin, et al. Requirement analyses and optimized design of wing/airfoil for aerospace vehicles[J]. 2021, 39(6): 101-110.
罗金玲, 龙双丽, 汤继斌, 等. 空天飞行器机翼/翼型的需求分析及应用[J]. 空气动力学学报, 2021, 39(6): 101−110. DOI： 10.7638/kqdlxxb-2021.0237

LUO Jinling, LONG Shuangli, TANG Jibin, et al. Requirement analyses and optimized design of wing/airfoil for aerospace vehicles[J]. 2021, 39(6): 101-110. DOI： 10.7638/kqdlxxb-2021.0237.

摘要

空天飞行器飞行空域大，速域宽，经历亚/跨/超/高超声速飞行，气动特性变化大，传统翼型难以同时满足低速、高速时的设计要求，给机翼/翼型设计提出了新的挑战。本文围绕飞行环境特点，分析了低速高升力与高速高升阻比、升重匹配、结构热防护等设计要求，提出了空天飞行器对机翼/翼型设计的新需求。基于一种新的宽速域翼型，采用数值模拟方法，开展三维流动下翼型与机翼平面形状的一体化优化设计，获得了一种翼型沿展向变化的新机翼，相对优化前，低速时机翼产生的升力效率提高了36.3%，超声速和高超声速升重平衡升阻比分别提高了33.4%和12.9%，新机翼能更好地兼顾低速、跨声速、超声速和高超声速气动性能的要求。将新机翼应用于典型空天飞行器，再通过全机气动外形优化设计，进一步提高了宽速域飞行时升重平衡下的使用升阻比，高亚声速时提高了5.9%，超声速时提高了10.3%，高超声速时提高了0.7%，解决了低速飞行时高升力与高速飞行时高升阻比的需求矛盾，并获得了一种满足宽速域总体设计要求的空天飞行器气动布局。研究成果具有一定工程指导意义。

Abstract

Aerospace vehicles have a wide velocity range that spans subsonic to hypersonic speeds. In such a wide speed range

their aerodynamic characteristics vary so significantly that traditional airfoils are improbable to satisfy the aerodynamic requirements for low- and high-speed flights at the same time. This paper proposes the requirements of airfoils and wings for aerospace vehicles

with especial attention being paid on the high lift at low speeds

high lift-to-drag ratio at high speeds

lift and gravity matching design

as well as structure and thermal protection design. In addition

an integrated design of airfoil and wing plane shape is carried out by numerical simulations based on a wide-speed-range airfoil. A new wing with spanwise-varying airfoils is obtained. Compared with the original wing

the lift efficiency of this new wing at low speed is increased by 36.3%. The lift-to-drag ratios at the lift-weight-balance point is increased by 33.4% and 12.9% respectively for supersonic and hypersonic flights. Since the new wing has good aerodynamic characteristics in the whole velocity range

it is further applied to a typical aerospace vehicle by an integrated optimization. The lift-to-drag ratio at the lift-weight-balance point is further improved by 5% at high subsonic speed

10.3% at supersonic speed

and 0.7% at hypersonic speed. The contradiction between high lift at low speed and high lift-to-drag ratio at high speed is alleviated. An aerospace vehicle layout that meets the overall design requirements for wide-speed-range flight is obtained. The results have certain engineering guiding significance.

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Keywords

references

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