Aerodynamic design and aerodynamic characteristic tests of a high-aspect-ratio flying-wing standard model
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摘要:
为校验高速风洞流场品质以及完善大展弦比飞翼布局飞行器的CFD算法验证体系，解决传统标模难以适配新型飞翼布局气动特性研究的问题，本文介绍了自主设计的大展弦比飞翼标模以及在2.4 m暂冲型跨声速风洞完成的气动力测量试验情况。重点分析了边界层转捩对大展弦比飞翼类布局气动特性试验结果的影响、2.4 m暂冲型跨声速风洞在大展弦比飞翼类布局气动力测量的试验精度、典型试验状态下模型弹性变形量等，并对大展弦比飞翼标模的基本纵横航向气动特性进行了介绍。结果表明大展弦比飞翼标模具有良好的气动性能，能够作为大展弦比飞翼布局飞行器研究标模，通过持续构建的气动数据库和研究结果，可有力支撑大展弦比飞翼气动布局流动机理认知、雷诺数效应、气动弹性等一系列相关空气动力学研究，并可有效支撑新型风洞试验技术开发、CFD技术验证与确认等研究。
Abstract:Aerodynamic evaluation of a self-developed high-aspect-ratio flying wing standard model was conducted in a 2.4 m transonic blowdown wind tunnel. The tests quantified boundary layer transition effects, assessed measurement system precision, and characterized elastic deformations under critical test conditions. Longitudinal and lateral-directional aerodynamic performance analyses confirmed the model’s stability and suitability as a benchmark for high-aspect-ratio flying wing configurations. The derived aerodynamic database elucidates flow mechanisms, Reynolds number dependencies, and aeroelastic behaviors specific to such configurations. Additionally, the study validates advanced wind tunnel testing methodologies while supplying critical testdatasets for computational fluid dynamics (CFD) code verification. Findings underscore the model’s utility in advancing integrated testcomputational frameworks for next-generation aircraft development, particularly in addressing aerodynamic complexities of high-aspect-ratio flying wings.
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Key words:
- aerodynamic characteristics /
- flying-wing /
- wind tunnel test /
- high-aspect-ratio /
- standard model
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图 1 大展弦比飞翼第一轮气动布局设计方案
Figure 1. First round aerodynamic layout design for high-aspect-ratio flying-wing
图 2 大展弦比飞翼气动方案迭代外形示意图
Figure 2. Schematic of aerodynamic configuration iteration for the high-aspect-ratio flying-wing
图 6 自由转捩与固定转捩试验结果对比（Ma=0.75, Rec=3.13×106）
Figure 6. Comparison of test results between natural transition and fixed transition （Ma=0.75, Rec=3.13×106）
图 7 重复性试验结果（Ma=0.75, Rec=3.13×106）
Figure 7. Results of repeated tests （Ma=0.75, Rec=3.13×106）
图 8 7次重复性试验的方均根误差（Ma=0.75, Rec=3.13×106）
Figure 8. Root mean square error of seven repeated tests （Ma=0.75, Rec=3.13×106）
图 9 全机基本纵向气动特性
Figure 9. Basic longitudinal aerodynamic characteristics of the whole aircraft
图 10 全机基本横航向气动特性
Figure 10. Basic lateral aerodynamic characteristics of the whole aircraft
图 13 大展弦比飞翼标模弦长和相对厚度沿展向的分布
Figure 13. Distributions of chord length and relative thickness along the span for the high-aspect-ratio flying-wing standard model
表 1 大展弦比飞翼布局气动外形迭代方案典型几何参数对比
Table 1. Comparison of typical geometric parameters for iterative aerodynamic configuration schemes of high-aspect-ratio flying-wing layout
几何特征参数 第一轮
布局第二轮布局
初始外形第二轮布局
优化外形翼展/m 53.6 85.3 85 中央翼根弦（机长）L/m 26.9 42.9 43 参考重心距离机头 Xg/m 16.14 24.6 23.1704 平均气动弦长Ca/m 15.27 9.36 9.3843 展弦比 Ar 5.1 9.1 10 前缘后掠角（外翼）Λl.e./（°） 33 37 37 后缘后掠角（外翼）Λt.e./（°） 0，18 28.6 28 面积（全面积）Sref/m2 563 1397 1394.8 
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表 2 Ma=0.75条件下气动力测量精度
Table 2. Force test accuracy at Ma=0.75
α σCL σCD σCm −2 0.0008 0.00008 0.0006 0 0.0006 0.00004 0.0004 2 0.0008 0.00002 0.0004 4 0.0005 0.00004 0.0004 6 0.0010 0.00013 0.0004 8 0.008 0.00025 0.0007 10 0.0054 0.00023 0.0051
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