翼反角对高压捕获翼构型高超气动特性的影响

doi:10.7527/S1000-6893.2022.27349

Abstract

Abstract:

To study the influence of wing dihedral/anhedral angle changes on the hypersonic aerodynamic characteristics of the High-pressure Capturing Wing （HCW） configuration， we studied the variation law of the lift-drag characteristics， and longitudinal and lateral-directional stability with the change of wing dihedral/anhedral angles based on a HCW concept configuration under the computation conditions of Mach number 6 and an altitude of 30 km. The design variables are dihedral/anhedral angles of HCW and delta wings， and some techniques， such as the uniform experimental design method， numerical simulation method， and Kriging modeling method， were utilized in the analysis. The results show that the lift， drag， and lift-drag ratio have similar variation trends with the change of wing dihedral/anhedral angles， and are more sensitive to the change of the dihedral angle. At small angles of attack， the wing dihedral significantly reduces the lift-drag ratio， while the anhedral slightly increases and then slowly decreases it. At large angles of attack， the wing dihedral/anhedral angles have less influence on the lift-drag ratio. The longitudinal stability is mainly affected by the dihedral/anhedral angles of the delta wing. Specifically， the delta wing dihedral decreases the longitudinal stability， while the anhedral hardly affects it. Both the wing dihedral and anhedral angles improve the directional stability， with the effect of the anhedral stronger. The wing dihedral raises the lateral stability， while the anhedral lowers it. However， at a large angle of attack， the large dihedral angle of the delta wing may lead to a decrease in lateral stability.

Key words: High-pressure Capturing Wing (HCW), hypersonic, aerodynamic characteristics, dihedral/anhedral angles, stability

CLC Number:

V221⁺.3

Siyuan CHANG, Yao XIAO, Guangli LI, Zhongwei TIAN, Kaikai ZHANG, Kai CUI. Effect of wing dihedral and anhedral angles on hypersonic aerodynamic characteristics of high-pressure capturing wing configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(8): 127349-127349.

Figures/Tables 22

Fig. 1

Fig. 2

Table 1

Fig. 3

Fig. 4

Table 2

Design variables and space

Design variables	Lower bound/（°）	Upper bound/（°）
$θ h c w$	-20	20
$θ b w$	-50	50

Table 2

Fig. 5

Fig. 6

Fig. 7

Fig. 8

Table 3

Table 4

Table 5

Fig. 9

Fig. 10

Fig. 11

Fig. 12

Fig. 13

Fig. 14

Fig. 15

Fig. 16

Fig. 17

References 29

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几何参数	数值
机体轴向长度/mm	1 000
HCW轴向长度/mm	490
HCW半展长/mm	400
HCW前缘后掠角/（°）	30
HCW尾缘后掠角/（°）	20
HCW装配角/（°）	3.5
HCW和机体三角翼厚度/mm	2
机体上表面压缩角/（°）	9
机体下表面压缩角/（°）	6
机体三角翼后掠角/（°）	70
机体尾段纵向膨胀角/（°）	18

Parameter	Coarse	Medium	Refined
C_L	0.270 6	0.271 5	0.270 9
ΔC_L /%	-0.11	0.21
C_D	0.088 5	0.089 9	0.089 8
ΔC_D /%	-1.44	0.06
C_m	-0.006 13	-0.005 98	-0.005 97
ΔC_m /%	2.68	0.17

Parameter	Coarse	Medium	Refined
X_ac	0.644 74	0.642 97	0.643 32
ΔX_ac/%	0.22	-0.05
C_lβ	-0.027 50	-0.026 07	-0.025 78
ΔC_lβ /%	6.67	1.11
C_nβ	-0.003 72	-0.004 58	-0.004 58
ΔC_nβ /%	-18.75	0

Output	α/（°）	MAE	MRE/%
C_L	0	4.0×10^-5	0.21
	5	1.8×10^-4	0.51
	10	2.8×10^-4	0.48
C_D	0	4.0×10^-5	1.61
	5	2.0×10^-5	0.25
	10	1.6×10^-4	0.86
C_lβ	0	3.6×10^-4	0.44
	5	4.2×10^-4	0.38
	10	6.6×10^-4	0.47
C_nβ	0	4.0×10^-4	1.67
	5	8.2×10^-4	2.89
	10	1.1×10^-3	2.77
X_ac	0	4.2×10^-4	1.24
X_ac	5	2.0×10^-4	0.48

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Effect of wing dihedral and anhedral angles on hypersonic aerodynamic characteristics of high-pressure capturing wing configuration

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