Aerodynamic design of nacelle of blended-wing-body aircraft with distributed propulsion
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摘要:
整流罩设计对基于分布式动力的翼身融合（BWB）飞机气动特性会产生显著影响。为了揭示在边界层吸入（BLI）效应下整流罩的设计参数对飞机气动特性的影响及其原因，采用计算流体力学（CFD）方法和Morris敏感度分析法对此布局飞机气动特性进行了详细研究，得到了整流罩主要设计参数对飞机气动特性影响的敏感度和耦合关系，并对典型设计参数下的流动特性进行分析。结果表明：对飞机气动特性影响较大的参数是整流罩特征截面2和3的最大厚度，这是因为其增大了当地截面的厚度和弯度，进而影响了整流罩表面的压力分布；在流量系数减小和进气边界弦向位置前移时，最大厚度增大会造成背风面发生局部分离；整流罩特征截面2和3的最大厚度对气动特性具有较强的耦合影响。
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关键词:
- 翼身融合(BWB)布局 /
- 边界层吸入(BLI) /
- 计算流体力学(CFD) /
- 敏感度分析 /
- 整流罩
Abstract:Nacelle design has a significant effect on aerodynamic performance of blended-wing-body (BWB) aircraft with distributed propulsion. To clarify the effect and its reason of primary nacelle design parameters on aerodynamic performance of BWB aircraft with boundary layer ingestion (BLI) effect, a detailed study was conducted by computational fluid dynamics (CFD) method and Morris sensitivity analysis method. Sensitivity order and coupled effect of primary design parameters on aerodynamic performance were obtained. Flow details of higher sensitivity and greater coupled effect parameters were analyzed under baseline and alternative condition. The results show that the relatively most significant parameters are the maximum thickness of section 2 and 3. The main reason is that local thickness and camber increase, and pressure distribution of whole nacelle surface is changed. Leeward local stall will occur as the maximum thickness increases configuration when mass flow rate decreases and inlet location along the chord direction moves forward. The coupled effect of the maximum thickness of section 2 and 3 on aerodynamic performance is relatively significant.
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图 1 分布式动力BWB飞机的气动布局
Figure 1. Aerodynamics configuration of distributed propulsion BWB aircraft
图 4 Morris法计算的各参数对气动系数影响的均值与标准差
Figure 4. Mean values and standard deviations of effects of parameters on aerodynamic coefficients with Morris method
图 7 t2变化时的各截面压力分布
Figure 7. Pressure distribution on cross sections with variation of t2
图 9 x4变化时的各截面压力分布
Figure 9. Pressure distribution on cross sections with variation of x4
图 10 不同τ下气动系数随t2的变化
Figure 10. Variation of aerodynamic coefficients with t2 at different τ
图 12 不同MFR下气动系数随t2的变化
Figure 12. Variation of aerodynamic coefficients with t2 at different MFR
图 13 MFR=0.40时飞机表面和对称面压力云图及喷口流线图
Figure 13. Pressure contours of aircraft surface and symmetric plane and stream lines of nozzle at MFR=0.40
图 14 不同Lf下气动系数随t2的变化
Figure 14. Variation of aerodynamic coefficients with t2 at different Lf
图 15 Lf=0.70时飞机表面和对称面压力分布及喷口流线图
Figure 15. Pressure contours of aircraft surface and symmetric plane and stream lines of nozzle at Lf=0.70
图 16 t2和t3耦合变化时的压力分布
Figure 16. Pressure distribution with coupled variation of t2 and t3
表 1 网格规模验证
Table 1. Validation of mesh size
算例名称 网格规模 CL CD 网格1 907 563 0.411 2 0.021 63 网格2 1 378 251 0.413 7 0.020 71 网格3 2 055 448 0.416 0 0.020 56 
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表 2 壁面网格高度验证
Table 2. Validation of wall grid height
算例名称 壁面网格高度/m CL CD 网格2 5×10-4 0.413 7 0.020 71 网格4 1×10-3 0.414 8 0.020 52 网格5 3×10-4 0.413 9 0.020 76
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表 3 参数的实际变化区间
Table 3. Actual changing interval of parameters
参数 Pi [Pi -l, Pi +u] ti(i=1, 2, 3, 4) 0.047 [0.007, 0.107] xi(i=1, 2, 3, 4) 0.29 [0.25, 0.35]
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表 4 t2对气动系数的影响
Table 4. Effect of t2 on aerodynamic coefficients
t2 CL CD CM 0.007 0.411 3 0.019 72 0.037 6 0.047 0.413 7 0.020 71 0.044 9 0.087 0.416 4 0.022 02 0.052 7
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表 5 x4对气动系数的影响
Table 5. Effect of x4 on aerodynamic coefficients
x4 CL CD CM 0.25 0.413 5 0.020 70 0.044 7 0.29 0.413 7 0.020 71 0.044 9 0.33 0.413 7 0.020 68 0.044 8
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表 6 基本设计参数的区间敏感度排序
Table 6. Interval sensitivity order of basis design parameters
参数 CL CD 流量系数 1.8 0.525 排气方向 1.34 0.32 进气边界弦向位置 0.392 0.28 进气边界高度 0.068 6 0.04 弦向整流罩长度 0.025 7 0.038 6 展向流量分布 0.019 5 0.024 展向进气位置分布 0.006 8 0.027
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表 7 t2和t3对气动系数的耦合影响
Table 7. Coupled effect of t2 and t3 onaerodynamic coefficients
气动系数 算例 dcoup dline 
CL 1 -0.012 4 -0.009 8 -21.1 2 -0.028 7 -0.002 1 -92.8 CD 1 -0.002 6 0.003 2 24.4 2 -0.003 8 -0.004 7 21.3 CM 1 0.045 2 -0.041 8 -7.5 2 -0.040 5 -0.019 1 -147.1 注：算例1、2分别代表t2和t3同时减少和同时增加。
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