Aeroelastic correction for nonlinear aerodynamic data in wind tunnel tests
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摘要: 介绍了一种在静气弹分析中引入CFD数据进行风洞数据非线性段弹性修正的方法。将多个迎角的CFD数据作为外部气动力引入NASTRAN静气弹分析，计算不同迎角（升力）区间内的气动导数并得到分段弹刚比，积分得到未变形模型的气动特性曲线。对大展弦比翼身组合体模型在不同动压和马赫数下的风洞试验结果进行弹性修正，结果表明：该方法显著提高了升力和力矩曲线非线性段的修正精度；在风洞试验的迎角范围内，与动压外插结果吻合，升力和力矩的最大误差不超过0.015和0.005；不同马赫数和动压下的修正结果表明该方法具有广泛的适用性，能够兼顾效率和精度，具有大规模应用的潜力。Abstract: A correction method for model deformation effects in wind tunnel tests is developed based on NASTRAN static aeroelastic analysis integrated with CFD data. Flexible To Rigid Ratio (FTR) of longitudinal aerodynamic derivatives for different angles of attack are calculated by NASTRAN with CFD correction, which is used to obtain aerodynamic characteristics of the undeformed model. Corrected aerodynamic characteristics of a high-aspect-ratio wingbody model under different circumstances of Mach number and dynamic pressure suggest that the proposed method largely improves the correction in the nonlinear part of CL and Cm curve. A minor discrepancy exists between corrected data and extrapolated results at different dynamic pressures, which is at most 0.015 for CL and 0.005 for Cm respectively. Moreover, the method is robust enough to gain accurate corrected results under different circumstances and efficient enough for large scale application in aircraft design.
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图 1 使用偶极子网格切割的CFD表面网格
Figure 1. CFD surface mesh cut by the DLM panels uncut CFD mesh and cut CFD mesh
图 3 计算模型与风洞测量变形结果对比
Figure 3. Comparison of displacement and rotation between NASTRAN model and wind tunnel measurement
图 5 Ma = 0.85工况下CL – α修正结果和误差
Figure 5. Corrected CL – α curve and deviation at Ma = 0.85
图 6 Ma = 0.80工况下CL – α曲线修正结果和误差
Figure 6. Corrected CL – α curve and deviation at Ma = 0.80
图 8 Ma = 0.85工况下Cm – α曲线修正结果和误差
Figure 8. Corrected Cm – α curve and deviation at Ma = 0.85
图 9 Ma = 0.80工况下Cm – α曲线修正结果和误差
Figure 9. Corrected Cm – α curve and deviation at Ma = 0.80
表 1 计算模型与风洞测量变形结果对比
Table 1. Comparison of displacement and rotation between NASTRAN model and wind tunnel measurement
翼尖变形 风洞测量 计算模型 误差 位移/mm 11.2592 10.4803 0.7789 扭转角/(°) −0.9240 −0.8255 0.0984 
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表 2 Ma = 0.85工况下CL – α曲线修正误差
Table 2. Deviation of corrected CL – α curve at Ma = 0.85
q/E =
0.38 × 10−6Ave. ΔCL Advantage Max ΔCL Advantage Fixed KCL 0.0075 — 0.0245 — Piecewise KCL 0.0055 −26.7% 0.0137 −44.2%
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表 3 Ma = 0.80工况下CL – α曲线修正误差
Table 3. Deviation of corrected CL–α curve at Ma=0.80
q/E =
0.36 × 10−6Ave. ΔCL Advantage Max ΔCL Advantage Fixed KCL 0.0047 — 0.0153 — Piecewise KCL 0.0043 −8.9% 0.0108 −29.7%
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表 4 Ma = 0.85工况下Cm – α曲线修正误差
Table 4. Deviation of corrected Cm – α curve at Ma = 0.85
q/E =
0.38 × 10−6Ave. ΔCm Advantage Max ΔCm Advantage Fixed KCm 0.0030 — 0.0174 — Piecewise KCm 0.0014 −53.7% 0.0043 −75.5%
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表 5 Ma=0.80工况下Cm–α曲线修正误差
Table 5. Deviation of corrected Cm–α curve at Ma=0.80
q/E =
0.38 × 10−6Ave. ΔCm Advantage Max ΔCm Advantage Fixed KCm 0.0021 — 0.0061 — Piecewise KCm 0.0018 −12.0% 0.0050 −18.1%
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表 6 Ma = 0.85工况下的弹性修正一致性
Table 6. Consistency of elastic correction at Ma = 0.85
Ave. ΔCL Max ΔCL Ave. ΔCm Max ΔCm Discrepancy 0.0030 0.0078 0.0008 0.0024
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表 7 计算步骤表
Table 7. Main procedure of correction
编号 计算步骤 计算资源 每个算例
耗时1 CFD计算，迎角0°、2°、3°、4°、5°，
多重网格计算5000步16核CPU工作站 4 h 2 CFD数据映射至气动面元 移动工作站 5 min 3 生成各迎角（升力）区间修正矩阵 移动工作站 5 min 4 NASTRAN静气弹分析 移动工作站 5 min
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