DLR-F11高升力构型的数值模拟

doi:10.19596/j.cnki.1001-246x.8612

摘要/Abstract

摘要：

基于国家数值风洞(NNW)风雷软件(PHengLEI), 针对AIAA第二届高升力会议DLR-F11全机构型开展气动特性数值模拟, 以评估软件对复杂高升力外形低速流动模拟能力。研究内容主要包括网格收敛性分析、雷诺数影响分析, 以及缝翼滑轨和襟翼滑轨整流罩影响分析。通过与试验结果、其他参考值对比分析表明: 对高升力外形, 软件在线性段的计算结果具有较高可信度, 在失速迎角附近的模拟结果也与参考值相当, 在考虑滑轨和滑轨整流罩等复杂构型后, 也能正确捕捉到关键分离流动特征。

关键词: 高升力构型, 计算流体力学, 风雷软件, 大迎角流动

Abstract:

In order to evaluate the simulation capability of the National Numerical Wind-tunnel CFD software PHengLEI for subsonic flows over the complex high lift configuration, the 2nd AIAA High-Lift Prediction Workshop DLR-F11 configuration is selected and simulated. The grid convergence analysis, the Reynolds number effects and the influence of the slat track as well as the flap track faring are presented. The comparison with the experimental data and reference values indicates that the results have good credibility and validity in the linear segment before stall, and the results near angle of stall agree well with reference values. With the additional components of the slat track and the flap track fairing, separated flow features on the wing can be correctly captured.

Key words: high lift configuration, computatinal fluid dynamics, NNW-PHengLEI, high alpha flows

郭勇颜, 曾志春, 何磊, 何乾伟, 严雪琴, 赵钟. DLR-F11高升力构型的数值模拟[J]. 计算物理, 2023, 40(4): 401-415.

Yongyan GUO, Zhichun ZENG, Lei HE, Qianwei HE, Xueqin YAN, Zhong ZHAO. Numerical Simulation of DLR-F11 High-lift Configuration[J]. Chinese Journal of Computational Physics, 2023, 40(4): 401-415.

图/表 21

表1 DLR-F11构型几何尺寸

Table 1 The geometry details of DLR-F11 model

Main dimensions	Half span/m	Wing Ref. area/m²	MAC/m	Aspect ratio	Taper ratio	0.25 Chord sweep/°	Fuselage length/m
Value	1.4	0.419 13	0.347 09	-9.353	0.3	30	3.077

图1 DLR-F11几何构型(a) Case 1几何构型；(b)Case 2几何构型；(c) Case 1部件；(d) Case 2部件

Fig.1 The geometry of DLR-F11 model (a) configuration of Case 1; (b) configuration of Case 2; (c) component of Case 1; (d) component of Case 2

图2 Case 1的计算网格(a) 粗；(b) 中；(c) 细

Fig.2 Three types of computational grids of Case 1 (a) coarse; (b) medium; (c) fine

图3 Case 2的计算网格(a) 物面网格；(b) 缝翼滑轨；(c) 襟翼滑轨整流罩

Fig.3 Computational grids of Case 2 (a) surface grid; (b) slat track; (c) flap track faring

表2 DLR-F11计算网格信息

Table 2 Details of computational grids of DLR-F11

	grid name	单元数/10⁶	节点数/10⁶	第一层网格高度/(10^-7 m)
Case 1	coarse	15.15	5.99	7.0
	medium	24.87	8.71	6.1
	fine	38.65	12.36	5.3
Case 2	coarse	42.87	16.19	6.1
	medium	84.91	38.78	4.3
	fine	170.32	59.09	3.1

图4 Case 1网格收敛性分析(a) 升力系数；(b) 阻力系数

Fig.4 Grid convergence analysis for Case 1 (a) CL; (b) CD

图5 压力系数展向站位示意图

Fig.5 Sketch map of spanwise locations of pressure coefficient

图6 Case 1中7°迎角下典型站位的物面压力系数分布(a) 28.8%站位；(b) 54.3%站位；(c) 75.1%站位；(d) 89.1%站位(左：缝翼; 中：主翼; 右：襟翼)

Fig.6 Pressure coefficient distribution at typical locations for Case 1 with α=7° (a)spanwise location =28.8%;(b) spanwise location =54.3%; (c) spanwise location =75.1%;(d)spanwise location =89.1% (left: slat; middle: wing; right: fllap)

图7 Case 2Ⅱ高雷诺数下不同网格密度升力系数计算与试验结果

Fig.7 Lift coefficients between CFD and experiment for Case 2 Ⅱ under different grid densities

图8 Case 2气动力系数计算与试验结果(a) 升力系数随迎角变化；(b) 阻力系数随迎角变化；(c) 升力系数随阻力系数变化

Fig.8 Aerodynamic coefficient between CFD and experiment for Case 2 (a) CL vs α; (b) CD vs α; (c)CL vs CD

图9 低雷诺数Case 2Ⅰ气动力系数计算与参会结果(a) 升力系数随迎角变化；(b) 阻力系数随迎角变化；(c) 升力系数随阻力系数变化

Fig.9 Aerodynamic coefficient between PHengLEI and the other CFD softwares for Case 2Ⅰ(a) CL vs α; (b) CD vs α; (c)CL vs CD

图10 高雷诺数Case 2Ⅱ气动力系数计算与参会结果(a) 升力系数随迎角变化；(b) 阻力系数随迎角变化；(c) 升力系数随阻力系数变化

Fig.10 Aerodynamic coefficient between PHengLEI and the other CFD softwares for Case 2Ⅱ(a) CL vs α; (b) CD vs α; (c)CL vs CD

图11 Case 2，7°迎角下典型站位的物面压力系数分布(a)28.8%站位；(b) 54.3%站位；(c) 75.1%站位；(d) 89.1%站位(左：缝翼; 中：主翼; 右：襟翼)

Fig.11 Pressure coefficient distribution at typical locations for Case 2 with α=7° (a)spanwise location =28.8%;(b) spanwise location =54.3%; (c) spanwise location =75.1%; (d)spanwise location =89.1%(left: slat; middle: wing; right: fllap)

图12 Case 2, 18.5°迎角下典型站位的物面压力系数分布(a)28.8%站位；(b) 54.3%站位；(c) 75.1%站位；(d) 89.1%站位(左：缝翼; 中：主翼; 右：襟翼)

Fig.12 Pressure coefficient distribution at typical locations for Case 2 with α=18.5° (a) spanwise location =28.8%;(b) spanwise location =54.3%; (c) spanwise location =75.1%; (d) spanwise location =89.1%.(left: slat; middle: wing; right: fllap)

图13 Case 2Ⅰ壁面极限流线与试验油流图(a) 7°迎角；(b) 18.5°迎角；(c) 21°迎角

Fig.13 Surface streamlines between CFD and experiment for Case 2Ⅰ (a) α=7°; (b) α=18.5°; (c) α=21°

图14 Case 2Ⅱ空间流线(湍流粘性系数着色) (a) 16°迎角；(b) 18.5°迎角；(c) 21°迎角；(d) 22.4°迎角

Fig.14 Streamlines for space distribution for Case 2Ⅱ (colored by turbulent viscosity)(a) α=16°; (b) α=18.5°; (c) α=21°; (d) α=22.4°

图15 速度型位置示意图

Fig.15 Sketch map of locations of velocity profiles

图16 Case 2Ⅰ, 7°迎角下典型位置速度型分布(a) R1B1；(b) R1B2；(c) R2E1；(d) R2E2

Fig.16 Velocity profiles at typical locations for Case 2 Ⅰ with α=7° (a) R1B1;(b) R1B2; (c) R2E1; (d) R2E2

图17 Case 2Ⅰ, 18.5°迎角下典型位置速度型分布(a) R1B1；(b) R1B2；(c) R2E1；(d) R2E2

Fig.17 Velocity profiles at typical locations for Case 2Ⅰ with α=18.5° (a) R1B1; (b) R1B2; (c) R2E1; (d) R2E2

图18 21°迎角96%站位处压力分布(a) 缝翼；(b) 主翼；(c) 襟翼

Fig.18 Pressure coefficient distribution between Case 1 and Case 2Ⅱ at 96% span location with α=21° (a) slat; (b) wing; (c) flap

图19 21°迎角壁面极限流线(a) Case 1无滑轨；(b) Case 2Ⅱ有滑轨

Fig.19 Surface streamlines between Case 1 and Case 2Ⅱ with α=21° (a) Case 1: model with no slat track; (b) Case 2Ⅱ: model with the slat track

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