航空学报2025，Vol.46Issue(14)：103-130,28.DOI:10.7527/S1000-6893.2025.31451
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
Integrated design of waverider forebody and inward-turning inlet considering viscous effect under given flowfield distribution
摘要
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 ef-fect.In terms of basic flowfield design improvement,the total pressure distribution of the reflected shock wave is im-proved 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 distri-bution on the upper wall,the central body of the new basic flowfield becomes a tapered surface,the intensity of the re-flected 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 re-flected 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 re-sults 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 axi-symmetric configuration verification example shows that the proposed method can improve the profile correction accu-racy and reduce the deviation from the inviscid design performance target.This method is applied to the viscosity cor-rection 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 im-proved,the strength of the reflected shock wave in the internal contraction section and the shock wave train in the iso-lation section is decreased,and the separation area of the internal flow channel caused by the boundary layer interfer-ence of the shock wave is reduced.The flow coefficient at the design point is increased by 3.22%,and the total pres-sure 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 signifi-cantly 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.关键词
乘波前体/内转式进气道/基准流场设计/黏性修正/一体化设计Key words
waverider forebody/inward-turning inlet/basic flowfield design/viscosity correction/integrated design分类
航空航天引用本文复制引用
付俊杰,屈峰,孙迪..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[J].航空学报,2025,46(14):103-130,28.基金项目
国家自然科学基金(11972308,52272378) （11972308,52272378）
西北工业大学博士论文创新基金(CX2023001) National Natural Science Foundation of China(11972308,52272378) （CX2023001）
Innovation Foundation for Doctor Dissertation of Northwestern Polytechnical University(CX2023001) （CX2023001）
