面向高超声速飞行器的宽速域翼型优化设计

张阳; 韩忠华; 周正; 汤继斌; 张科施; 宋文萍

doi:10.7638/kqdlxxb-2021.0384

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面向高超声速飞行器的宽速域翼型优化设计

翼型研究新进展 | 更新时间：2026-05-28

- 面向高超声速飞行器的宽速域翼型优化设计
- Aerodynamic design optimization of wide-Mach-number-range airfoils for hypersonic vehicles
- 空气动力学学报 2021年39卷第6期页码：111-127
- 作者机构：
  
  1. 西北工业大学气动与多学科优化设计研究所,西安,710072
  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
  3. 中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,绵阳,621000
  4. 北京空天技术研究所,北京,100074
- 作者简介：
  
  张阳（1996-），男，湖北宜昌人，博士生，研究方向：高超声速飞行器宽速域气动优化设计方法. E-mail：1559695483@qq.com
  韩忠华*（1977-），男，四川资中人，博士，教授，博士生导师，研究方向：飞行器设计空气动力学. E-mail: hanzh@nwpu.edu.cn
- 基金信息：
  
  国家自然科学基金（11972305）;航空基金（2019ZA053004）;陕西省自然科学基金（2020JM-127）;陕西省杰出青年科学基金（2020JC-31）
- DOI：10.7638/kqdlxxb-2021.0384
  中图分类号： V211.41
- 纸质出版：2021
- 稿件说明：
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张阳, 韩忠华, 周正, 等. 面向高超声速飞行器的宽速域翼型优化设计[J]. 空气动力学学报, 2021, 39(6): 111−127.

ZHANG Yang, HAN Zhonghua, ZHOU Zheng, et al. Aerodynamic design optimization of wide-Mach-number-range airfoils for hypersonic vehicles[J]. 2021, 39(6): 111-127.
张阳, 韩忠华, 周正, 等. 面向高超声速飞行器的宽速域翼型优化设计[J]. 空气动力学学报, 2021, 39(6): 111−127. DOI： 10.7638/kqdlxxb-2021.0384

ZHANG Yang, HAN Zhonghua, ZHOU Zheng, et al. Aerodynamic design optimization of wide-Mach-number-range airfoils for hypersonic vehicles[J]. 2021, 39(6): 111-127. DOI： 10.7638/kqdlxxb-2021.0384.

摘要

宽速域气动设计是水平起降高超声速飞行器研制的瓶颈问题之一。水平起降高超声速飞行器在飞行过程中需要经历亚、跨、超和高超声速多个速域，而适应不同速域的最佳气动外形相互矛盾，使得实现良好的宽速域气动设计面临极大挑战。首先，针对高超声速飞行器宽速域翼型气动设计问题，发展了基于代理模型的高效全局气动优化设计方法，并设计出一种相对厚度为4%、有一定弯度、下表面具有双“S”形特征的宽速域翼型。将新翼型与常规四边形和双弧形翼型进行了气动特性对比，并进行了流动机理分析，结果表明新翼型的宽速域综合气动特性显著优于常规翼型，从而证明发展兼顾亚、跨、超和高超声速气动性能的宽速域翼型是可行的。其次，开展了宽速域翼型的多目标优化设计，通过分析Pareto解集中翼型的宽速域气动性能随几何外形变化的演化规律，进一步解释了有一定弯度、下表面呈双“S”形的薄翼型能够协调亚、跨、超声速与高超声速气动性能的原理。最后，采用平面外形为梯形的机翼，进行了三维机翼构型下的宽速域翼型多目标优化设计。三维优化设计结果与二维结果具有相似的几何特征和压力分布，说明这种通过下表面双“S”形小弯度薄翼型来兼顾亚、跨、超和高超声速气动性能的宽速域流动机理同样适用于三维情况，也证实了翼型设计对于宽速域高超声速飞行器仍然具有重要意义。

Abstract

Wide-Mach-number-range aerodynamic design is one of the bottlenecks in the development of horizontal take-off and landing hypersonic vehicles which experience subsonic

transonic

supersonic

and hypersonic regimes during their flights. However

optimized airfoil profiles for different speed regimes are often contradictory

which presents a great challenge to obtain satisfactory wide-Mach-number-range aerodynamic performance by a single configuration. Consequently

this article is aimed at the design of wide-Mach-number-range airfoils via an efficient global aerodynamic optimization design method based on surrogate models. First

a new wide-Mach-number-range airfoil is designed by taking both the hypersonic and transonic aerodynamic performance into account. The thickness of the optimal airfoil is 4%

and its lower surface features a double-"S" shape. Flow-field analyses indicate that the optimal airfoil compromises aerodynamic performance over a wide speed range

which has not been observed before. Second

a multi-objective optimization design of airfoils is further carried out

and a Pareto front of the lift-to-drag ratios from the transonic to hypersonic states is obtained. By analyzing the optimal results

the design principle of airfoils that compromises transonic and hypersonic aerodynamic performance is explained. Finally

the multi-objective optimization design of airfoils for three-dimensional wings is carried out. It is shown that the optimized airfoil for three-dimensional configurations has geometric characteristics similar to those obtained by two-dimensional optimization design

indicating that the flow mechanism around airfoils with small chambers and double-"S" lower surfaces also applies to three-dimensional situations and that the airfoil design is still of significance for wide-Mach-number-range hypersonic vehicles.

关键词

Keywords

references

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