远程民机变弯度机翼后缘外形变形矩阵气动设计

doi:10.7527/S1000-6893.2022.27335

Abstract

Abstract:

Aerodynamic optimization research on the trailing edge deformation matrix is conducted for the long-range civil aircraft variable camber wing. Geometric parameterization of the deformation shape is determined in combination with the features of knuckle deformation structures，and the aerodynamic optimization design process of the trailing edge deformation matrix is established considering deformational coupling constraints on the basis of surrogate-based optimization algorithm. The deformation matrix for cruise flight profile characterized by lift step variations，and the deformation matrix for non-cruise flight profile composed of the buffeting point and drag divergence point are then obtained. The results show that：the drag reduction benefit of trailing edge deformation for cruise flight profile increased while the lift variation relative to the base point increased，and that the drag reduction quantity in a high lift state is about 7-8 times that in a low lift state. The key to trailing edge deformation drag reduction is to adjust the pressure distribution of the main wing. Since it is not sensitive to the deflection angle of deformation shape control sections，considering deformational coupling constraints has no remarkable impact on drag reduction benefit. Additionally，the step deformation matrix with the same deflection law of the trailing edge deformation shape，a linear corresponding relationship between the deflection angle and design lift，and obvious drag reduction benefit does exist. For the non-cruise flight profile deformation matrix，significant regularity is found from trailing edge deformation as that of cruise flight profile deformation matrix，and the trailing edge shape deformation can effectively reduce the shock wave intensity at the buffeting point，but not for the drag divergence point.

Key words: long-range civil aircraft, variable camber wing, trailing edge deformation matrix, aerodynamic design, surrogate-based optimization

CLC Number:

V211.3

Chunpeng LI, Zhansen QIAN, Xiasheng SUN. Trailing edge deformation matrix aerodynamic design for long-range civil aircraft variable camber wing[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 127335-127335.

Figures/Tables 31

Fig. 1

Fig. 2

Fig. 3

Fig. 4

Fig. 5

Fig. 6

Fig. 7

Fig. 8

Table 1

Fig. 9

Table 2

Fig. 10

Table 3

Table 4

Fig. 11

Fig. 12

Table 5

Fig. 13

Fig. 14

Fig. 15

Fig. 16

Table 6

Drag coefficient reduction of step deformation matrix trailing edge deformation under trimmed condition（Ma = 0.85，H = 11 km）

C_L	$Δ C D 1$	$Δ C D 2$
0.576	0.001 46	-0.000 01
0.528	0.000 74	0
0.480	0.000 11
0.432	0.000 07	-0.000 02
0.384	0.000 18	0

Table 6

Table 7

New added design points drag coefficient reduction of step deformation matrix trailing edge deformation under trimmed condition（Ma = 0.85，H = 11 km）

C_L	$Δ C D 1$	$Δ C D 3$	$Δ C D 4$	$Δ C D 5$
0.562	0.001 22
0.547	0.001 02	0.000 99		0.000 91
0.533	0.000 82
0.518	0.000 59
0.504	0.000 39	0.000 35	0.000 33
0.490	0.000 20

Table 7

Fig. 17

Table 8

Fig. 18

Fig. 19

Fig. 20

Table 9

Fig. 21

Fig. 22

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参数	取值
C_L	0.4，0.5，0.6，0.7，0.8，0.9
单变量取值范围	中弧线旋转角度变量（-10 ~ 10）
4变量取值范围	中弧线比例分段变量（0.15 ~ 0.6）
	前段中弧线旋转角度变量（-10 ~ 10）
	中段中弧线旋转角度变量（-10 ~ 10）
	后段中弧线旋转角度变量（-10 ~ 10）

设计升力系数C_L	单变量	4变量
设计升力系数C_L	中弧线旋转角度量	中弧线分段变量	前段中弧线旋转角度变量	中段中弧线旋转角度变量	后段中弧线旋转角度变量
0.4	-1.5	0.327	-6.11	8	-6.7
0.5	-0.8	0.24	0.163	-1.57	-2
0.6	-0.1	0.2	-0.85	2.27	-2.53
0.7	0	0.5	0	0	0
0.8	0.8	0.287	3.16	-2.52	1.57
0.9	1.4	0.182	6.7	-5.69	3.35
1.0	1.7	0.387	4.81	-5	5.42

C_L	非配平		配平
C_L	ΔC_D	α/（°）	ΔC_D	α/（°）	δ_tail/（°）
0.576	0.001 40	1.85	0.001 48	1.81	-0.44
0.528	0.000 62	1.68	0.000 75	1.62	-0.05
0.432	0.000 03	1.59	0.000 10	1.48	0.59
0.384	0.000 17	1.41	0.000 18	1.30	0.84

状态	C_L	ΔC_D	α/（°）	δ_tail/（°）
非配平	0.48	0.000 25	1.726
配平	0.48	0.000 11	1.543	-0.097

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Trailing edge deformation matrix aerodynamic design for long-range civil aircraft variable camber wing

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C_L	下边界逐渐缩小		上下边界同时缩小
C_L	ΔC_D	ΔDC_D	ΔC_D	ΔDC _D
0.576	0.001 48	0	0.001 48	0
0.528	0.000 70	0.000 05	0.000 74	0.000 01
0.432	0.000 08	0.000 02	0.000 09	0.000 01
0.384	0.000 18	0	0.000 18	0