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CLC number: V211.1

On-line Access: 2020-06-11

Received: 2020-01-17

Revision Accepted: 2020-04-29

Crosschecked: 2020-07-15

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Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Shao-hua Chen

https://orcid.org/0000-0002-6244-5131

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Journal of Zhejiang University SCIENCE A 2020 Vol.21 No.9 P.770-782

http://doi.org/10.1631/jzus.A2000020


Design methodology of an osculating cone waverider with adjustable sweep and dihedral angles


Author(s):  Shao-hua Chen, Jun Liu, Wei Huang, Feng Ding

Affiliation(s):  Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   chenshaohua_nudt@163.com, liujun@nudt.edu.cn

Key Words:  Osculating cone waverider, Planform leading-edge profile curve, Sweep and dihedral angles, Lift-to-drag ratio, Lateral static stability


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Shao-hua Chen, Jun Liu, Wei Huang, Feng Ding. Design methodology of an osculating cone waverider with adjustable sweep and dihedral angles[J]. Journal of Zhejiang University Science A, 2020, 21(9): 770-782.

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Abstract: 
When considering the practical engineering application of a waverider, the on-design and off-design aerodynamic characteristics of the design conditions, especially the lift-to-drag ratio and the stability, deserve attention. According to recently studies, the planform and rear sight shape of a waverider are closely related to the above aerodynamic performance. Thus, the planform leading-edge profile curve used to design the planform shape of a vehicle is applied to designing an osculating cone waverider. Two key parameters concerned in planform and rear sight shape, namely the plan view sweep angle of the leading edge and the dihedral angle of the underside are introduced to the waverider design process. Each parameter is inserted in the control curve equation. Especially, a parameterization scheme is put forward for the free adjustment of the sweep angle along the leading edge. Finally, three examples are generated for verification and investigation. After the verification process based on the inviscid flow field of one case, the influences of the sweep and dihedral angles on the lift-to-drag ratio and the lateral static stability are evaluated, and meaningful results are obtained. Based on these results, we can conclude that, considering the maximum lift-to-drag ratio, the sweep angle plays a role on the lift-to-drag ratio only at subsonic and trans/supersonic speed as a negligible effect is observed at hypersonic speeds, whereas the dihedral angle is seem to produce a relevant difference at hypersonic speeds. Considering the lateral static stability, the dihedral angles have more influence on the waverider than the sweep angles.

后掠角及反角可控的吻切锥乘波体设计方法

目的:在飞行器设计中,后掠角及反角会对飞行器的升阻比及横向静稳定性带来影响. 本文基于吻切锥乘波体设计方法,将后掠角及反角引入到乘波体的设计过程中,以期实现吻切锥乘波体后掠角及反角的可控设计.
创新点:1. 通过理论推导建立后掠角及反角与吻切锥乘波体设计中前缘线在水平面投影型线以及激波底部型线的关系; 2. 通过数值计算,研究后掠角及反角研究对吻切锥乘波体升阻比及横向静稳定性的影响.
方法:1. 引入基于水平投影型线的吻切锥乘波体设计方法,给出一种前缘点求解方案(图2和4); 2. 通过理论推导,构建设计参数(后掠角与反角)与乘波体设计输入型线的关系(公式(10)和(11)); 3. 通过数值模拟,验证设计方法的可行性和有效性(图14和15),以及分析非设计点和设计点下后掠角及反角对乘波体升阻比及横向静稳定性的影响(图17~19,21~23).
结论:1. 考虑到最大升阻比,后掠角仅在亚音速和跨/超音速时对升阻比起作用,在高超音速时其影响几乎可以忽略; 2. 在高超音速时,反角会对升阻比产生影响; 3. 对于乘波器的设计,考虑横向静稳定性时,反角比后掠角更重要; 4. 下反角有利于横向静稳定性.

关键词:吻切锥乘波体; 前缘线水平投影型线; 后掠角; 反角; 升阻比; 横向静稳定性

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