涡波效应宽速域气动外形设计

doi:10.7527/S1000-6893.2017.21824

Abstract

Abstract: This paper extends the concept of the osculating-cone waverider. The global geometrical relationships between the inlet capture curve, flow capture tube and planform contour line are derived to develop the design for the planform-controllable waverider. The vortex effect is introduced by customizing the planform for the waverider. The concept of aerodynamic width-velocity-range design with vortex-shock effects is proposed, meaning employing the vortex effect under subsonic condition and the shock effect under the super/hypersonic condition to ensure a general performance. The CFD technology is used to simulate the aerodynamic performance of the double swept configuration at the subsonic and hypersonic states. A comparison with the flat plate model with respect to the lift, drag and flow characteristics at the subsonic and supersonic states is made. Simulation results show that the planform-controllable waverider has satisfying performance under both subsonic and hypersonic condition, overcoming some deficiencies of the traditional waverider, and providing insight into the width-velocity-range design.

Key words: waverider, planform-controllable, vortex and shock effect, shock wave, width-velocity-range

CLC Number:

V211.3

LIU Chuanzhen, LIU Qiang, BAI Peng, CHEN Bingyan, ZHOU Weijiang. Aerodynamic shape design integrating vortex and shock effects for width-velocity-range[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(7): 121824-121824.

References

[1] DIETRICH K. The aerodynamic design of aircraft:AIAA-2012-0448[R]. Reston, VA:AIAA, 2012.
[2] NONWEILER T R F. Aerodynamic problems of manned space vehicles[J]. Aeronautical Journal, 1959, 63(585):521-528.
[3] JONES J G, MOORE K C, PIKE J, et al. A method fo designing lifting configurations for high supersonic speeds using axisymmetric flow field[J]. Archive of Applied Mechanics, 1968, 37(1):56-72.
[4] RASMUSSEN M L. Waverider configurations derived from inclined circular and elliptic cones[J]. Journal of Spacecraft and Rockets, 1980, 17(6):537-545.
[5] LOBBIA M A, SUZZKI K. Experimental investiga-tion of a Mach 3.5 waverider designed using computa-tional fluid dynamics[J]. AIAA Journal, 2015, 53(6):1590-1601.
[6] SOBIECZKY H, DOUGHERTY F C, JONES K. Hyper-sonic waverider design from given shock waves[C]//In-ternational Hypersonic Waverider Symposium, 1990.
[7] MILLER D S, WOOD R M. Lee-side flow over delta wings at supersonic speed:NASA TP-2430[R]. Washington, D.C.:NASA, 1985.
[8] STARKEY R, LEWIS M. A simple analytical model for parametric studies of hypersonic waveriders:AIAA-1998-1616[R]. Reston, VA:AIAA, 1998.
[9] RODI E P. The osculating flowfield method of waverider geometry generation:AIAA-2005-0511[R]. Reston, VA:AIAA, 2005.
[10] RODI E P. Geometrical relationships for osculating cones and osculating flowfield waveriders:AIAA-2011-1188[R]. Reston, VA:AIAA, 2011.
[11] MOELDER S. Internal, axisymmetric, conical flow[J]. AIAA Journal, 1967, 5(7):1252-1255.
[12] 刘传振, 白鹏, 陈冰雁. 双后掠乘波体设计及性能优势分析[J]. 航空学报, 2017, 38(6):120808. LIU C Z, BAI P, CHEN B Y. Design and property advantages analysis of double swept waverider[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(6):120808(in Chinese).
[13] HUANG X Z, MEBARKI Y, BENMEDDOUR A, et al. Experimental and numerical studies of geometry effects on UCAV's aerodynamics:AIAA-2004-0403[R]. Reston, VA:AIAA, 2004.
[14] ROE P L. Approximate Riemann solvers, parameter vectors, and difference schemes[J]. Journal of Computational Physics, 1981, 43:357-372.
[15] VENKATA KRISHNAN V. On the accuracy of limiters and convergence to steady state solutions:AIAA-1993-0880[R]. Reston, VA:AIAA, 1993.
[16] KERMANI M J, PLETT E G. Modified entropy correction formula for the Roe scheme:AIAA-2001-0083[R]. Reston, VA:AIAA, 2001.
[17] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8):1598-1605.
[18] WANG Z J, CHEN R F. Fast, block lower-upper Symmet-ric Gauss-Seidel scheme for arbitrary grids[J]. AIAA Journal, 2000, 38(12):2238-2245.
[19] BOWCUTT K G. Optimization of hypersonic waveriders derived from cone flows-Including viscous effects[D]. Maryland:University of Maryland, 1986.
[20] PATRICK E R. Vortex lift waverider configurations:AIAA-2012-1238[R]. Reston, VA:AIAA, 2012.

Aerodynamic shape design integrating vortex and shock effects for width-velocity-range

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Yahui SONG, Gaoyu FAN, Lixia QU, Yuelin ZHANG, Yue XU, Shuo HAN. Progress of aircraft sonic boom flight test measurement technology: Review [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626186-626186.
[2]	Zheng LI, Cong XU, Jian ZHANG, Mengmeng LI, Yilei MA, Guanghui BAI. Reverse jet flow control by plasma synthetic jet actuator in high speed flow field [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 225-232.
[3]	CHENG Jianrui, SHI Chongguang, QU Lixia, XU Yue, YOU Yancheng, ZHU Chengxiang. Theoretical model of 2D curved shock wave/turbulent boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 125993-125993.
[4]	HAN Luyang, WANG Bin, PU Liang, CHEN Qing, ZHENG Haibin. Research progress on mechanism and related problems of energy deposition drag reduction technology [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 26032-026032.
[5]	LIU Chuanzhen, MENG Xufei, LIU Rongjian, BAI Peng. Experimental and numerical investigation of hypersonic performance of double swept waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126015-126015.
[6]	TONG Fulin, DONG Siwei, DUAN Junyi, LI Xinliang. Direct numerical simulation of separation bubble in shock wave/turbulent boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125437-125437.
[7]	ZHANG Haoyuan, SUN Dong, QIU Bo, ZHU Yandan, WANG Anling. Influence of turbulent kinetic energy on shock wave/boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125504-125504.
[8]	ZHOU Yan, LUO Zhenbing, WANG Lin, XIA Zhixun, GAO Tianxiang, XIE Wei, DENG Xiong, PENG Wenqiang, CHENG Pan. Plasma synthetic jet actuator for flow control: Review [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 25027-025027.
[9]	MENG Xufei, BAI Peng, LI Dun, WANG Rong, LIU Chuanzhen. Effect of dihedral wings on hypersonic performance of double swept waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(2): 124998-124998.
[10]	WANG Hongyu, YANG Yanguang, HU Weibo, CHEN Zhi, FENG Liming, ZHOU Youtian. Experimental study on unsteadiness characteristics of shock wave/turbulent boundary layer interaction controlled by high-frequency microsecond pulse discharge [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625905-625905.
[11]	GANG Dundian, YI Shihe, MI Qi, NIU Haibo. Experiment on interaction between supersonic turbulent boundary layer and cylinder [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 626104-626104.
[12]	XIE Zhuxuan, YANG Yanguang, WANG Gang. Structure of shock-induced separation in confined flow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 626042-626042.
[13]	DUAN Junyi, TONG Fulin, LI Xinliang, LIU Hongwei. Decomposition of mean friction drag in compression-expansion turbulent boundary layer [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625915-625915.
[14]	FAN Xiaohua, TANG Zhigong, WANG Gang, YANG Yanguang. Review of low-frequency unsteadiness in shock wave/turbulent boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625917-625917.
[15]	SHI Xiaotian, LYU Meng, ZHAO Yuan, TAO Shancong, HAO Le, YUAN Xiangjiang. Flow control technique for shock wave/turbulent boundary layer interactions [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625929-625929.