基于离散伴随的高超声速密切锥乘波体气动优化设计

doi:10.7527/S1000-6893.2022.26664

Abstract

Abstract:

The design method of osculating-cone waverider based on planform-controllable shape can significantly improve the design flexibility and overall lift-drag characteristics for traditional waveriders. However， because the three-dimensional effect， the viscous effect and the passivation effect of the head/leading edge are ignored in the design of the waverider， overflow still occurs under the design conditions leading to the difficulty in achieving the optimal lift-to-drag ratio. In addition， the lift-drag characteristics will still be poor when the waverider is not in design conditions. In this paper， an aerodynamic shape optimization design method for the hypersonic vehicle based on discretized adjoint is constructed by combining the CFD solvers based on the full-velocity flux solution method and the RANS turbulence model， the robust automatic structured mesh wrapping method， the free form deformation geometry parameterization method， the discretized adjoint method and the sequential quadratic programming algorithm. Through this method， the single point and multi-point three-dimensional aerodynamic optimization designs of the whole aircraft are carried out for the planform-controllable osculating-cone waverider. Under more than 4 million structural grids， 600 design variables and 303 design constraints， the proposed method only takes 2 240 CPU hours and 3 360 CPU hours to achieve the single point and multi-point optimization designs of the waverider. The results show that compared with the initial configuration， the lift-drag ratio of the single point optimization configuration in the design state increased by nearly 5%. The configuration obtained by multipoint optimization can ensure that the lift-drag ratio at off-design states is increased by more than 10% without loss of lift-drag characteristics at design state， which improves the theoretical limitations of the planform-controllable osculating-cone waverider to a certain extent.

Key words: hypersonic, aerodynamic optimization design, discretized adjoint, osculating-cone waverider, planform-controllable

CLC Number:

V211

Chaoyu LIU, Feng QU, Di SUN, Chuanzhen LIU, Zhansen QIAN, Junqiang BAI. Discretized adjoint based aerodynamic optimization design for hypersonic osculating-cone waverider[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(4): 126664-126664.

Figures/Tables 26

Fig. 1

Fig. 2

Fig. 3

Table 1

Grid independent compute results of waverider

网格	$C L$	$C D$	相对细网格的误差/%
粗	1.111 56	0.224 43	1.7
中	1.112 53	0.223 63	1.3
细	1.089 64	0.220 68	0

Table 1

Fig. 4

Fig. 5

Fig. 6

Table 2

Table 3

Comparison of pressure center positions before and after optimization （single point optimization）

构型	$x c p$ /%
位移差	0
初始	65.4
优化	65.4

Table 3

Fig. 7

Fig. 8

Fig. 9

Fig. 10

Fig. 11

Table 4

Table 5

Fig. 12

Fig. 13

Fig. 14

Fig. 15

Fig. 16

Fig. 17

Fig. 18

Fig. 19

Fig. 20

Fig. 21

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构型	C_L	C_D	C_Dp	C_Df	C_L /C_D
相对变化/%	-1.2	-5.8	-6.9	-2.6	+4.9
初始	1.111 49	0.228 30	0.174 49	0.053 81	4.869
优化	1.097 81	0.214 97	0.162 52	0.052 44	5.107

构型	C_L			C_D			C_L /C_D
构型	α₁=0°	α₂=2°	α₃=6°	α₁=0°	α₂=2°	α₃=6°	α₁=0°	α₂=2°	α₃=6°
初始	0.110 71	0.436 14	1.111 49	0.087 11	0.107 47	0.228 30	1.271	4.058	4.869
优化	0.151 14	0.477 46	1.131 31	0.084 26	0.107 10	0.230 00	1.794	4.458	4.920
相对变化/%	+36.5	+9.5	+1.8	-3.4	-0.3	+0.7	+41	+10	+1

构型	C_M			x_cp/%
构型	α₁=0°	α₂=2°	α₃=6°	α₁=0°	α₂=2°	α₃=6°
位移差				-15.4	-2.7	-0.8
初始	0.632 2	1.900 2	4.577 2	92.1	69.7	65.4
优化	0.719 1	1.998 1	4.601 5	76.7	67.0	64.6

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Discretized adjoint based aerodynamic optimization design for hypersonic osculating-cone waverider

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