定流场分布下考虑黏性效应的乘波前体/内转式进气道一体化设计

doi:10.7527/S1000-6893.2025.31451

Abstract

Abstract:

The integrated configuration of the waverider forebody and inward turning inlet is one of the mainstream choices for the long-range hypersonic cruise vehicle due to its great high-speed lift-drag characteristics， superior inflow capture ability and high compression efficiency. To improve the performance of the integrated configuration， this paper proposes an integrated design method based on improving the basic flowfield design and considering the viscous effect. In terms of basic flowfield design improvement， the total pressure distribution of the reflected shock wave is improved to a quadratic distribution which can reduce the gradient of the total pressure distribution. After giving the anti-tangent Mach number distribution on the upper wall and the Bezier flow angle distribution on the center body wall， the high-total-pressure-recovery internal compression basic flowfield with the controllable flow field distribution in the whole flow channel is designed. Compared with the local inverse design basic flowfield with only a given Mach number distribution on the upper wall， the central body of the new basic flowfield becomes a tapered surface， the intensity of the reflected shock wave is greatly reduced， and the total pressure recovery coefficient is greater than 0.98. The resulting integrated configuration maintains the characteristics of the basic flowfield while exhibiting lower strength of the reflected shock wave in the inner contraction section and the shock wave train in the isolation section and the reduced proportion of the low energy region at the exit. Consequently， the lift-to-drag ratio at the design point increase by 15.16%， the total pressure recovery coefficient at exit increase by 3.33%， and the distortion at exit decrease by 4.62%. In terms of the consideration of the viscous effect， this paper combines the high-fidelity numerical solution results with the displacement thickness calculation formula of the axisymmetric boundary layer to carry out the viscosity correction. Compared with the traditional two-dimensional plate boundary layer viscosity correction method， the axisymmetric configuration verification example shows that the proposed method can improve the profile correction accuracy and reduce the deviation from the inviscid design performance target. This method is applied to the viscosity correction of the original configuration to obtain a modified configuration. Compared with the original configuration， the closure of the forebody shock wave and the incident shock wave at the lower lip of the modified configuration is improved， the strength of the reflected shock wave in the internal contraction section and the shock wave train in the isolation section is decreased， and the separation area of the internal flow channel caused by the boundary layer interference of the shock wave is reduced. The flow coefficient at the design point is increased by 3.22%， and the total pressure recovery coefficients of the throat and exit at the design point are increased by 2.41% and 0.31%， respectively. Moreover， the aerodynamic performances at the lift-weight balance point and in the wide-speed range are also significantly improved. In summary， the integrated design of waverider forebody / inward turning inlet proposed in this paper offers better lift-drag and flow-capture performance， providing valuable insight for the aerodynamic design of the long-range hypersonic cruise vehicle.

Key words: waverider forebody, inward-turning inlet, basic flowfield design, viscosity correction, integrated design

CLC Number:

V211.4

Junjie FU, Feng QU, Di SUN. Integrated design of waverider forebody and inward-turning inlet considering viscous effect under given flowfield distribution[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(14): 131451.

Figures/Tables 80

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Table 1

Initial parameters of internal compression basic flowfield

参数	$δ i$ /（°）	$r C B$ /m	$a m$	$b m$	$c m$
数值	3	0.125	1	2	-0.1
参数	$σ (r E)$	$σ (r D)$	$δ x 1$		$δ x 2$
数值	0.999	0.98	5		5

Table 1

Fig.12

Fig.13

Fig.14

Fig.15

Table 2

Design conditions of internal compression basic flowfield

参数	$M a 2$	$P 2$ / $P a$	$ρ 2$ /（kg·m^-3）	$T 2 / K$	$R e 2$
数值	5.17	6 005.97	0.073 02	286.59	7 189 474

Table 2

Fig.16

Fig.17

Fig.18

Fig.19

Fig.20

Fig.21

Fig.22

Fig.23

Fig.24

Table 3

Calculation results of MOC for internal compression basic flowfield

参数	$σ t$	$P t h r o a t / P 2$	CR	ICR	$L t$
数值	0.984 22	9.702 36	4.583 85	1.766 71	4.897 86

Table 3

Fig.25

Fig.26

Fig.27

Table 4

Performance parameters of two internal compression basic flowfields

构型	$σ t$	$P t h r o a t / P 2$	CR	ICR	$L t$
Base1	0.983 5	9.820 3	4.583 8	1.766 7	4.897 9
Base2	0.947 4	11.267 8	4.982 4	1.920 3	4.620 0

Table 4

Fig.28

Fig.29

Fig.30

Fig.31

Table 5

Fig.32

Fig.33

Fig.34

Table 6

Fig.35

Fig.36

Fig.37

Fig.38

Table 7

Fig.39

Table 8

Different mesh sizes and calculation results

网格	网格量	C_L	C_D	$σ t h r o a t$	$σ o u t$
粗	1 872 300	0.070 4	0.039 5	0.724 4	0.584 7
中	6 319 040	0.070 7	0.039 1	0.727 7	0.577 4
细	21 326 760	0.070 8	0.039 1	0.729 2	0.572 6

Table 8

Fig.40

Fig.41

Fig.42

Fig.43

Fig.44

Fig.45

Table 9

Table 10

Table 11

Comparison of inviscid flow capture performance

构型	$σ t h r o a t$	$P t h r o a t / P ∞$	$M a t h r o a t$	$σ o u t$	$P o u t / P ∞$	$M a o u t$	$φ$
Geo_Base1_Inviscid	0.904 4	26.888 2	3.273 9	0.883 2	27.216 8	3.240 6	0.997
Geo_Base2_Inviscid	0.871 0	30.265 1	3.143 6	0.854 7	33.194 9	3.079 7	0.997

Table 11

Fig.46

Fig.47

Fig.48

Fig.49

Fig.50

Table 12

Comparison of flowfield distortion index

构型	$D I t h r o a t$	$D I o u t$
Geo_Base1_Inviscid	0.800 2	0.612 3
Geo_Base2_Inviscid	0.975 3	0.642 0

Table 12

Table 13

Inviscid and viscous intake performance of configuration Geo_Base1_Inviscid

类型	$σ t h r o a t$	$P t h r o a t / P ∞$	$σ o u t$	$P o u t / P ∞$	φ
无黏	0.904 4	26.888 2	0.883 2	27.216 8	0.997
黏性	0.727 7	34.420 5	0.577 4	39.844 5	0.962

Table 13

Table 14

Comparison of intake performance at design point before and after viscous correction

构型	$σ t h r o a t$	$P t h r o a t / P ∞$	$σ o u t$	$P o u t / P ∞$	φ
修正前	0.727 7	34.420 5	0.577 4	39.844 5	0.962
修正后	0.745 2	28.395 1	0.579 2	32.714 8	0.993

Table 14

Fig.51

Fig.52

Fig.53

Fig.54

Table 15

Fig.55

Fig.56

Table 16

Fig.57

Table 17

Comparison of viscous results at CL =0.070 73

构型	C_L	C_D	L/D	φ	$σ t h r o a t$	$P t h r o a t / P ∞$	$σ o u t$	$P o u t / P ∞$
Geo_Base1_Inviscid	0.070 73	0.039 12	1.807 9	0.962	0.727 7	34.420 5	0.577 4	39.844 5
Geo_Base1_Correction	0.070 73	0.038 12	1.855 5	1.004	0.739 5	28.996 4	0.578 3	33.442 0

Table 17

Fig.58

Table 18

Fig.59

Table 19

Comparison of viscous results at non-design point Ma∞=5

构型	C_L	C_D	L/D	φ	$σ t h r o a t$	$P t h r o a t / P ∞$	$σ o u t$	$P o u t / P ∞$
Geo_Base1_Inviscid	0.087 52	0.041 18	2.124 9	0.813 4	0.769 8	28.831 7	0.655 8	32.628 7
Geo_Base2_Inviscid	0.088 64	0.044 46	1.993 7	0.801 6	0.740 3	33.419 1	0.618 4	39.501 6
Geo_Base1_Correction	0.082 59	0.038 80	2.128 4	0.848 9	0.785 7	23.958 9	0.666 9	26.243 0

Table 19

Fig.60

Table 20

Comparison of viscous results at non-design point Ma∞=4.5

构型	C_L	C_D	L/D	φ	$σ t h r o a t$	$P t h r o a t / P ∞$	$σ o u t$	$P o u t / P ∞$
Geo_Base1_Inviscid	0.094 01	0.043 01	2.185 7	0.741 3	0.765 7	28.272 6	0.645 1	31.828 5
Geo_Base1_Correction	0.091 14	0.040 78	2.234 6	0.770 9	0.796 7	22.172 8	0.672 0	24.807 1

Table 20

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指标	无黏	有黏	mod-Axi	mod-Flat
壁面压升	2.495 3	2.536 6	2.495 8	2.466 3
相对偏差	0	1.656%	0.019%	-1.164%

指标	无黏	有黏	mod-Axi	mod-Flat
σ_t	0.983 5	0.900 3	0.909 4	0.908 7
P_throat/P₂	9.820 3	11.190 0	9.320 7	9.272 8

构型	S₀/m²	S₁/m²	S₂/m²	CR	ICR
Geo_Base1_Inviscid	0.17	0.131 9	0.019 1	8.919	1.902
Geo_Base2_Inviscid	0.17	0.131 9	0.017 8	9.431	2.012
Geo_Base1_Correction	0.17	0.134 1	0.021 9	7.760	1.779

构型	上壁面	下壁面	增益
Geo_Base1_Inviscid	3.31	-4.28	-0.97
Geo_Base2_Inviscid	3.65	-4.68	-1.03

构型	ICR	SI
Geo_Base1_Inviscid	1.902	0.823 814 058
Geo_Base2_Inviscid	2.012	0.777 103 911
Geo_Base1_Correction	1.779	0.882 885 242

Integrated design of waverider forebody and inward-turning inlet considering viscous effect under given flowfield distribution

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构型	C_L	C_D	L/D
Geo_Base1_Inviscid	0.080 55	0.025 39	3.172 1
Geo_Base2_Inviscid	0.073 77	0.026 78	2.754 6

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[3]	Jun CHEN, Feng QU, Junjie FU. Design method of hypersonic inward turning inlet based on genetic and gradient hybrid optimization strategy [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 130808-130808.
[4]	Lili CHEN, Jianxia LIU, Juntao ZHANG, Zheng GUO, Anping WU, Zhongxi HOU. Waverider forebody design method with longitudinal segments and multi-stage compression [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(4): 128744-128744.
[5]	Dingchong LYU, Shoujun ZHAO, Si ZENG, Jian FU, Xintong HU, Huixiang LIU, Kefei MIAO, Yongling FU. Key technologies and challenges of high⁃performance servo⁃motor⁃pumps [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(15): 630225-630225.
[6]	Weihong ZHANG, Han ZHOU, Shaoying LI, Jihong ZHU, Lu ZHOU. Material⁃structure integrated design for high⁃performance aerospace thin⁃walled component [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 627428-627428.
[7]	Shuai HAO, Tielin MA, Yi WANG, Jinwu XIANG, Hongzhong MA, Baifeng JIANG, Jun CAO. Progress and application of key technologies of SensorCraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 27034-027034.
[8]	Yuanyuan TU, Dayi WANG, Xiangyan ZHANG, Jiaxing LI, Xiaofeng HUANG. Reconfigurability and autonomous reconfiguration methods of spacecraft [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 628855-628855.
[9]	Yulin DING, Zhonghua HAN, Jianling QIAO, Han NIE, Wenping SONG, Bifeng SONG. Research progress in key technologies for conceptual-aerodynamic configuration design of supersonic transport aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626310-626310.
[10]	Yongzhou LI, Di SUN, Renhua WANG, Kunyuan ZHANG. Design of inward turning inlet with controlled Mach number under non-uniform inflow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127857-127857.
[11]	WANG Zhixiang, LEI Yongjun, DUAN Jingbo, OUYANG Xing, ZHANG Dapeng, WANG Jie. Multi-region integrated design and optimization of concentrated-force diffusion component in heavy-lift launch vehicle [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 225135-225135.
[12]	ZHANG Wenhao, LIU Jun, DING Feng. Integrated design method of inward turning inlet/Von Karman waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(3): 123502-123502.
[13]	JIANG Yongsong, ZHENG Wentao, ZHAO Hang, YANG Mingsui, WANG Yongmei. Low noise design of fan outlet guide vane, part Ⅰ: Method and optimization [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 122955-122955.
[14]	ZHENG Wentao, JIANG Yongsong, ZHAO Hang, PAN Ruochi, ZHAO Yong. Low noise design of fan outlet guide vane, part Ⅱ: Numerical verifications [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 122956-122956.
[15]	SHEN Zhengyang, CHEN Xiaoming, HUANG Lingcai. Challenges for aircraft design due to special mission models of large-scale amphibious aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(1): 522400-522400.