CLC number: V22
On-line Access: 2019-12-09
Received: 2019-07-12
Revision Accepted: 2019-09-26
Crosschecked: 2019-11-13
Cited: 0
Clicked: 3722
Wen-hao Zhang, Jun Liu, Feng Ding, Wei Huang. Novel integration methodology for an inward turning waverider forebody/inlet[J]. Journal of Zhejiang University Science A, 2019, 20(12): 918-926.
@article{title="Novel integration methodology for an inward turning waverider forebody/inlet",
author="Wen-hao Zhang, Jun Liu, Feng Ding, Wei Huang",
journal="Journal of Zhejiang University Science A",
volume="20",
number="12",
pages="918-926",
year="2019",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A1900334"
}
%0 Journal Article
%T Novel integration methodology for an inward turning waverider forebody/inlet
%A Wen-hao Zhang
%A Jun Liu
%A Feng Ding
%A Wei Huang
%J Journal of Zhejiang University SCIENCE A
%V 20
%N 12
%P 918-926
%@ 1673-565X
%D 2019
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A1900334
TY - JOUR
T1 - Novel integration methodology for an inward turning waverider forebody/inlet
A1 - Wen-hao Zhang
A1 - Jun Liu
A1 - Feng Ding
A1 - Wei Huang
J0 - Journal of Zhejiang University Science A
VL - 20
IS - 12
SP - 918
EP - 926
%@ 1673-565X
Y1 - 2019
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A1900334
Abstract: In this study, an inward turning waverider forebody/inlet axisymmetric reference flow model with a conical leading-edge shock wave was designed based on the method of characteristics. The design eliminates the lip shock wave at the shoulder point. Based on the reference flow model, a novel integrated design method for an inward turning waverider forebody/inlet is proposed. The streamline tracing method and related technologies were used to generate the integrated configuration in the reference flow model. During the design process, the inward turning inlet was divided into an upper and a lower surface. After the formation of these surfaces, the front external surface and the lip external surface were simultaneously generated. Finally, an integrated configuration was formed with these four generated surfaces and a base plane. An analysis of the formed configuration was carried out using numerical simulation software, which verified the correctness and feasibility of the method. The conclusions drawn from the research indicate that the integrated design method is feasible and effective.
The authors present a novel methodology for designing inward turning inlets (ITI). The topic of ITI is of great interest in the hypersonic airbreathing community. The reviewer finds the paper to be well written. The authors show a high pressure recovery in their design. Challenging areas of design include off-design performance such as different Mach number and incidence angle, and viscous effects including shock/boundary layer interactions.
[1]ANSYS Inc., 2010. Ansys Fluent 13.0 Theory Guide. ANSYS Inc., Canonsburg, USA.
[2]Barkmeyer DEF, Starkey RP, Lewis MJ, 2005. Inverse waverider design for inward turning inlets. Proceedings of the 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
[3]Billig FS, Kothari AP, 2000. Streamline tracing: technique for designing hypersonic vehicles. Journal of Propulsion and Power, 16(3):465-471.
[4]Ding F, Liu J, Shen CB, et al., 2015. Novel inlet-airframe integration methodology for hypersonic waverider vehicles. Acta Astronautica, 111:178-197.
[5]Ding F, Liu J, Shen CB, et al., 2018. An overview of waverider design concept in airframe/inlet integration methodology for air-breathing hypersonic vehicles. Acta Astronautica, 152(1):639-656.
[6]Ferguson F, Dasque N, Mrema HF, et al., 2015. A coupled aerodynamic and propulsive performance analysis of the generic hypersonic vehicle. Proceedings of the 51st AIAA/SAE/ASEE Joint Propulsion Conference.
[7]Heiser WH, Pratt DT, 1994. Hypersonic Airbreathing Propulsion. AIAA, Washington, USA, p.24-26.
[8]Kothari AP, Tarpley C, McLaughlin TA, et al., 1996. Hypersonic vehicle design using inward turning flow fields. Proceedings of the 32nd Joint Propulsion Conference and Exhibit.
[9]Li YQ, An P, Pan CJ, et al., 2014. Integration methodology for waverider-derived hypersonic inlet and vehicle forebody. Proceedings of the 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.
[10]Li YQ, Shi CG, Zhu CX, et al., 2018. Aerodynamic combination design concept for hypersonic waverider forebody and inward turning inlet. Journal of Propulsion Technology, 39(10):2320-2328 (in Chinese).
[11]Liao L, Yan L, Huang W, 2018. Mode transition process in a typical strut-based scramjet combustor based on a parametric study. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 19(6):431-451.
[12]Qiao WY, Yu AY, Yang DW, 2018. Integration design of inward-turning inlets based on forebody shock wave. Acta Aeronautica et Astronautica Sinica, 39(10):60-71 (in Chinese).
[13]Tian C, Li N, Gong GH, et al., 2013. A parameterized geometry design method for inward turning inlet compatible waverider. Chinese Journal of Aeronautics, 26(5):1135-1146.
[14]Walker S, Tang M, Morris S, et al., 2008. Falcon HTV-3X–a reusable hypersonic test bed. Proceedings of the 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.
[15]Walker SH, Rodgers F, 2005. Falcon hypersonic technology overview. Proceedings of the AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference.
[16]Wang CP, Tian X, Yang LF, et al., 2015. Preliminary integrated design of hypersonic vehicle configurations including inward-turning inlets. Journal of Aerospace Engineering, 28(6):04014143.
[17]Wang JF, Cai JS, Liu CZ, et al., 2017a. Aerodynamic configuration integration design of hypersonic cruise aircraft with inward-turning inlets. Chinese Journal of Aeronautics, 30(4):1349-1362.
[18]Wang JF, Cai JS, Duan YH, et al., 2017b. Design of shape morphing hypersonic inward-turning inlet using multistage optimization. Aerospace Science and Technology, 66:44-58.
[19]Wang WX, Gu Q, Guo RW, 2017. Study of flow control of inward turning inlet. Journal of Propulsion Technology, 38(5):961-967 (in Chinese).
[20]Wang XD, Wang JF, Lyu ZJ, 2016. A new integration method based on the coupling of multistage osculating cones waverider and Busemann inlet for hypersonic airbreathing vehicles. Acta Astronautica, 126:424-438.
[21]Yang DW, Yu AY, Han YY, et al., 2019. Study on self-starting characteristics of an inward turning inlet. Journal of Propulsion Technology, 40(1):76-83 (in Chinese).
[22]Zhou H, Jin ZG, Zhang KY, 2018. Effects of entrance and exit aspect ratios on flow characteristics of inward turning inlets. Journal of Propulsion Technology, 39(12):2679-2684 (in Chinese).
[23]Zucrow MJ, Hoffman JD, 1977. Gas Dynamics, Vol. 2: Multidimensional Flow. John Wiley and Sons, Inc., New York, USA, p.112-294.
[24]Zuo FY, Huang GP, Xia C, et al., 2015. Investigation of the self-starting ability of an internal waverider inlet for ramjet. Proceedings of the 51st AIAA/SAE/ASEE Joint Propulsion Conference.
[25]Zuo FY, Huang GP, Xia C, 2016. Investigation of internal-waverider-inlet flow pattern integrated with variable-geometry for TBCC. Aerospace Science and Technology, 59:69-77.
Open peer comments: Debate/Discuss/Question/Opinion
<1>