Comprehensive design method for aerodynamic performance and stability of HWB configuration in large cargo aircraft

Zhang Ronghan; Liang Yu

doi:10.7638/kqdlxxb-2025.0090

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Comprehensive design method for aerodynamic performance and stability of HWB configuration in large cargo aircraft

更新时间：2026-10-14

- Comprehensive design method for aerodynamic performance and stability of HWB configuration in large cargo aircraft
- Vol. 44, Issue 8, Pages: 29-45(2026)
- 作者机构：
  
  1. 北京航空航天大学航空科学与工程学院,北京,100191
  2. 北京航空航天大学无人系统研究院,100083
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0090
  CLC： V221.3;V212.1
- Published：2026
- 稿件说明：
移动端阅览
张镕涵, 梁煜. 大型货机HWB布局气动性能与稳定性综合设计方法[J]. 空气动力学学报, 2026, 44(8): 29−45.

Zhang Ronghan, Liang Yu. Comprehensive design method for aerodynamic performance and stability of HWB configuration in large cargo aircraft[J]. 2026, 44(8): 29-45.
张镕涵, 梁煜. 大型货机HWB布局气动性能与稳定性综合设计方法[J]. 空气动力学学报, 2026, 44(8): 29−45. DOI： 10.7638/kqdlxxb-2025.0090

Zhang Ronghan, Liang Yu. Comprehensive design method for aerodynamic performance and stability of HWB configuration in large cargo aircraft[J]. 2026, 44(8): 29-45. DOI： 10.7638/kqdlxxb-2025.0090.

摘要

针对混合翼身融合布局飞机在大型货运领域的应用潜力，提出了一种兼顾气动效率与动稳定性的优化设计方法。以巡航阶段的升阻比和荷兰滚模态飞行品质为优化目标，构建气动/稳定性优化框架，采用带边界层修正的欧拉方程求解器进行快速分析，并结合高精度RANS求解器对优化结果进行验证。在对初始构型分析的基础上，通过优化框架对目标构型的气动效率和动稳定模态响应特性进行优化。RANS计算结果表明，在保持设计约束的前提下，气动优化构型的总阻力系数减小约3.5 counts，巡航升阻比由21.244提升至21.784，提升效率约为2.54%；考虑气动性能与动稳定性的双目标优化构型的总阻力系数减小约2.4 counts，巡航升阻比提升至21.609，提升效率约为1.72%，荷兰滚模态的阻尼比与无阻尼固有频率的乘积由

0.02633

提升至

0.05117

，依据MIL-F-8785C规范，飞行品质由最低三级提升至二级，横航向动稳定性获得显著改善。该优化框架实现了气动性能与动稳定性的有效权衡，为HWB布局大型货机的工程应用与优化提供了思路与参考。

Abstract

To explore the application potential of the Hybrid Wing Body (HWB) configuration in the field of large cargo aircraft

an optimization design method balancing aerodynamic efficiency and dynamic stability is proposed. Taking the lift-to-drag ratio and the Dutch roll mode flight quality during the cruise phase as optimization objectives

an aerodynamic/stability optimization framework is constructed. An Euler e

quation solver with boundary layer corrections is employed for rapid analysis

while a high-fidelity RANS solver is used to validate the optimization results. Based on the analysis of the initial configuration

the optimization framework is applied to enhance the aerodynamic efficiency and dynamic stability modal response characteristics of the target configuration. RANS calculation results show that

under the premise of maintaining design constraints

the total drag coefficient of the aerodynamically optimized configuration is reduced by approximately 3.5 counts

with the cruise lift-to-drag ratio increasing from 21.244 to 21.784

achieving an efficiency improvement of approximately 2.54%. For the configuration optimized with both aerodynamic performance and dynamic stability objectives

the total drag coefficient is reduced by approximately 2.4 counts

the cruise lift-to-drag ratio is improved to 21.609 with an efficiency increase of approximately 1.72%

and the product of the Dutch roll mode damping ratio and the undamped natural frequency is increased from

0.02633

to 0.05117. This improvement elevates the flight quality from Level 3 to Level 2 according to the MIL-F-8785C standard

significantly enhancing the lateral-directional dynamic stability. The optimization framework effectively balances aerodynamic performance and dynamic stability

providing insights and references for the engineering application and optimization of HWB-configured large cargo aircraft.

关键词

Keywords

references

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