DESIGN AND OPTIMIZATION FOR HYPERSONIC CONE-DERIVED WAVERIDER WITH BLUNTED LEADING-EDGE

Guo Shuaiqi; Liu Wen; Zhang Chen’an; Wang Famin

doi:10.6052/0459-1879-21-611

Volume 54 Issue 5

May 2022

Turn off MathJax

Article Contents

Article Navigation > Chinese Journal of Theoretical and Applied Mechanics > 2022 > 54(5): 1414-1428

Guo Shuaiqi, Liu Wen, Zhang Chen’an, Wang Famin. Design and optimization for hypersonic cone-derived waverider with blunted leading-edge. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1414-1428 doi: 10.6052/0459-1879-21-611

Citation:

Guo Shuaiqi, Liu Wen, Zhang Chen’an, Wang Famin. Design and optimization for hypersonic cone-derived waverider with blunted leading-edge. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1414-1428 doi: 10.6052/0459-1879-21-611

Citation:

PDF( 3910 KB)

DESIGN AND OPTIMIZATION FOR HYPERSONIC CONE-DERIVED WAVERIDER WITH BLUNTED LEADING-EDGE

doi: 10.6052/0459-1879-21-611

*.
State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
†.
School of Engineering Science, University of Chinese Academy of Sciences, Beijing 100049, China

Received Date: 2021-11-22
Accepted Date: 2022-02-18

Available Online: 2022-02-19

Publish Date: 2022-05-01

Abstract

Abstract

The waverider configuration has a broad application in hypersonic vehicles due to its high lift-to-drag ratio (L/D). In actuality, the sharp leading edge must be blunted because of the serious aerothermal heating problem, which can lead to significant loss of aerodynamic performance. Thus, the optimum configuration with sharp leading-edge cannot guarantee that it is still optimum after being blunted. To solve the problem, this paper first studies the influence and mechanism of leading-edge bluntness on the lift and drag characteristics of different configurations. The results show that the bluntness causes the lift to decrease slightly, the drag to increase greatly, and the L/D to decrease significantly. The wave drag of the blunted leading-edge plays a dominant role in the total drag increment, and the friction drag of the blunted leading-edge is very close to the friction drag reduction of the upper and lower surface. Based on the above results, this paper evaluates the wave drag of the blunted leading-edge by the modified Newton theory, and combines the aerodynamic models of sharp leading-edge waverider and genetic algorithm to obtain the optimum configurations with blunted leading-edge. The aerodynamic forces of the optimum configurations are evaluated via CFD simulation. The results show that under the constraints of different flight altitudes, different lift, and different blunt radii, compared with the optimum configurations with sharp leading-edge, the blunted optimized waveriders have the characteristics that the width is smaller, the sweep angle at the same longitudinal position is larger, and the L/D is higher. At the design condition of M_∞ = 15, H = 50 km and CL = 0.3, the L/D of the optimum blunted configuration with R = 10 mm can be improved by 9.32%. What’s more, as the constraint of the lift coefficient increases, blunt radius increases, and the flight altitude decreases, the advantage of L/D for the blunted optimized waveriders become more evident.
- hypersonic,
- waverider,
- leading-edge bluntness

FullText(HTML)

References(37)

References

[1]	Kuchemann D. The Aerodynamic Design of Aircraft. Oxford: Pergamon Press, 1978: 448-510
[2]	Nonweiler TRF. Aerodynamic problems of manned space vehicles. Journal of Royal Aeronautical Society, 1959, 63: 521-528 doi: 10.1017/S0368393100071662
[3]	Moore KC. The application of known flow fields to the design of wings with lifting upper surface at high supersonic speeds. RAE Technical Report, 1965
[4]	Jones JG, Moore KC, Pike J, et al. A method for designing lifting configurations for high supersonic speeds using axisymmetric flow fields. Archive of Applied Mechanics, 1968, 37: 56-72
[5]	Takashima N, Lewis MJ. Waverider configurations based on non-axisymmetric flow fields for engine-airframe integration//AIAA Aerospace Sciences Meeting & Exhibits, Reno, NV, 1994: 1-15
[6]	Sobieczky H, Dougherty FC, Jones K. Hypersonic waverider design from given shock waves//First International Hypersonic Waverider Symposium, University of Maryland, 1990: 1-19
[7]	Rodi PE. The osculating flowfield method of waverider geometry generation//43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2005: 1-8
[8]	贺旭照, 倪鸿礼. 密切内锥乘波体设计方法和性能分析. 力学学报, 2011, 43(5): 803-808 He Xuzhao, Ni Hongli, Osculating inward turning cone (OIC) wave rider-design methods and performance analysis. Chinese Journal of Theoretical and Applied Mechanics. 2011, 43(5): 803-808 (in Chinese))
[9]	贺旭照, 倪鸿礼. 密切曲面锥乘波体——设计方法与性能分析. 力学学报, 2011, 43: 1077-1082 He Xuzhao, Ni Hongli. Osculating curved cone waverider: Design methods and performance analysis. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(6): 1077-1082 (in Chinese)
[10]	卫峰, 丁国昊, 马志成等. 密切曲面锥导乘波体的设计与理论分析. 推进技术, 2021, 42(2): 298-308 (Wei Feng, Ding Guohao, Ma Zhicheng, et al. Design and theoretical analysis of osculating curve cone derived waverider. Journal of Propulsion Technology, 2021, 42(2): 298-308 (in Chinese)
[11]	Zheng XG, Hu Z, Li Y, et al. Local-turning osculating cones method for waverider design. AIAA Journal, 2020, 58(8): 3499-3513 doi: 10.2514/1.J059139
[12]	刘传振, 孟旭飞, 刘荣健等. 双后掠乘波体高超声速试验与数值分析. 航空学报, 2022, 43: 126015 (Liu Chuanzhen, Meng Xufei, Liu Rongjian, et al. Experimental and numerical investigation for hypersonic performance of double swept waverider. Acta Aeronautica et Astronautica Sinica, 2022, 43: 126015 (in Chinese)
[13]	刘传振, 白鹏, 王骥飞等. 给定前缘线平面形状的密切锥乘波体设计方法. 力学学报, 2019, 51(4): 991-997 (Liu Chuanzhen, Bai Peng, Bai Jifei, et al. Osculating-cone waverider design by customizing the planform shape of leading edge. Chinese Journal of Theoretical and Applied Mechanics, 2019, 51(4): 991-997 (in Chinese) doi: 10.6052/0459-1879-18-368
[14]	Hu SY, Jiang CW, Gao ZX, et al. Combined-wedge waverider for airframe-propulsion integration. AIAA Journal, 2018, 56(8): 3348-3352
[15]	Liu W, Zhang CA, Wang FM. Modification of hypersonic waveriders by vorticity-based boundary layer displacement thickness determination method. Aerospace Science and Technology, 2018, 75: 200-214
[16]	Liu J, Liu Z, Wen X, et al. Novel osculating flowfield methodology for wide-speed range waverider vehicles across variable Mach number. Acta Astronautica, 2019, 162(5): 160-167
[17]	Wang D, Wang JF, Li LF, et al. Novel volume-improved design method of large-slenderness-ratio cone-derived waveriders. AIAA Journal, 2020, 58(11): 4832-4847
[18]	吴乔, 卢笙, 叶友达等. 一种给定容积空间的乘波构型参数化设计方法. 空气动力学学报, 2019, 37(5): 754-761 (Wu Qiao, Lu Sheng, Ye Youda, et al. A parametric design method for the waverider configuration with given volume. Acta Aerodynamic Sinica, 2019, 37(5): 754-761 (in Chinese)
[19]	郑晓刚, 朱呈祥, 尤延铖. 基于局部偏转吻切方法的多级压缩乘波体设计. 力学学报, 2022, 54(1): 83-93 (Zheng Xiaogang, Zhu Chengxiang, You Yancheng. Design of multistage compression waverider based on the local- turning osculating cones method. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(1): 83-93 (in Chinese) doi: 10.6052/0459-1879-21-414
[20]	Liu W, Zhang CA, Wang XP, et al. Parametric study on lateral-directional stability of hypersonic waverider. AIAA Journal, 2021, 59(8): 3025-3042
[21]	Ding F, Liu J, Shen CB, et al. An overview of research on waverider design methodology. Acta Astronautica, 2017, 140: 190-205 doi: 10.1016/j.actaastro.2017.08.027
[22]	Zhao ZT, Huang W, Yan L, et al. An overview of research on wide-speed range waverider configuration. Progress in Aerospace Sciences, 2020, 113: 100606
[23]	Gillum MJ, Lewis MJ. Experimental results on a Mach 14 waverider with blunt leading edges. Journal of Aircraft, 1997, 34(3): 296-303 doi: 10.2514/2.2198
[24]	陈小庆, 侯中喜, 刘建霞等. 边缘钝化对乘波体性能影响分析. 宇航学报, 2009, 30(4): 1334-1339 (Chen Xiaoqing, Hou Zhongxi, Liu Jianxia, et al. The blunt leading edge’s influence to the performance of waverider. Journal of Astrunautics, 2009, 30(4): 1334-1339 (in Chinese) doi: 10.3873/j.issn.1000-1328.2009.04.005
[25]	Liu JX, Hou ZX, Ding GH, et al. Numerical and experimental study on waverider with blunt leading edge. Computers and Fluids, 2013, 84: 203-217 doi: 10.1016/j.compfluid.2013.06.005
[26]	Bowcutt KG, Anderson JD, Capriotti D. Viscous optimized hypersonic waveriders//AIAA 25th Aerospace Sciences Meeting, Reno, Nevada, 1987: 1-18
[27]	李维东, 韩汉桥, 陈文龙等. 考虑高空黏性干扰效应的乘波体气动性能工程预测方法研究. 宇航学报, 2011, 32(6): 1217-1223 (Li Weidong, Han Hanqiao, Chen Wenlong, et al. An engineering prediction method for aerodynamic performance of waverider with hypersonic viscous interaction. Journal of Astronautics, 2011, 32(6): 1217-1223 (in Chinese) doi: 10.3873/j.issn.1000-1328.2011.06.002
[28]	Tincher DJ, Burnett DW. Hypersonic waverider test vehicle: A logical next step. Journal of Spacecraft and Rockets, 1994, 31(3): 392-399 doi: 10.2514/3.26451
[29]	Liu W, Zhang CA, Han HQ, et al. Local piston theory with viscous correction and its application. AIAA Journal, 2017, 55: 942-954 doi: 10.2514/1.J055207
[30]	刘文. 高超声速乘波体气动布局优化及稳定性研究. [博士论文]. 西安: 西北工业大学, 2018 Liu Wen. Study on aerodynamic design optimization and flight stability of hypersonic waveriders. [PhD Thesis]. Xi’an: Northwestern Polytechnical University, 2018 (in Chinese)
[31]	Hammit AG, Bogdonoff SM. Hypersonic studies of the leading edge effect on the flow over a flat plate. Jet Propulsion, 1956, 26(4): 241-246
[32]	刘文, 张陈安, 王发民等. 高超声速“准乘波体”构型优化设计方法. 中国科学:技术科学, 2019, 49(3): 255-267 (Liu Wen, Zhang Chen’an, Wang Famin, et al. Design method of a new hypersonic waverider configuration. Scientia Sinica Technologica, 2019, 49(3): 255-267 (in Chinese) doi: 10.1360/N092017-00373
[33]	Cruz CI, Sova GJ. Improved tangent-cone method for the aerodynamic preliminary analysis system version of the hypersonic arbitrary-body program. NASA Technical Note, 1990
[34]	Bertram MH. Hypersonic laminar viscous interaction effects on the aerodynamics of two-dimensional wedge and triangular planform wings. NASA Technical Note, 1966
[35]	David DJ, Anderson JD. Reference temperature method and Reynolds analogy for chemically reacting non-equilibrium flowfields. Journal of Thermophysics and Heat Transfer, 1994, 89: 190-192
[36]	Anderson JD. Hypersonic and High-Temperature Gas Dynamics. 2nd ed. New York: McGraw-Hill Book Co, 2006
[37]	White FM. Viscous Fluid Flow. 3rd ed. New York: McGraw-Hill Book Co., 2006: 517