The dual-throat Ludwieg tube tunnel can effectively eliminate disturbances caused by the opening process of the fast-acting valve, but it will significantly reduce the effective running time of wind tunnel. Additionally, due to the limi-tations of the material of the fast-acting valve, it is difficult to further increase the heating temperature of the storage section of the Ludwieg tube tunnel. To solve this problem, this paper proposes a novel design for the dual-throat Ludwieg tube wind tunnel by placing the annular heater in the settling chamber to achieve an integrated design of flow uniformity and heating. Firstly, the unsteady numerical simulation is used to verify the feasibility of the dual-throat Ludwieg wind tunnel with new layout. Then, the start-up characteristics was analyzed, and the variation of Mach number and pressure at different stations during the running is quantitatively studied. Finally, the effect of the heater on the running process of the tunnel is explored. The results show that the effective running time of dual-throat Ludwieg tube tunnel with a heater in the settling chamber up to 80 ms, which can be increased by 23% com-pared to the traditional dual-throat layout. Additionally, when the heater temperature is increased from 434K to 1234K, the maximum deviation of Mach number in the core region at the exit of the second nozzle can be de-creased by 0.21%, the root mean square deviation can be decreased by 0.005, and the temperature can be in-creased by nearly 40K, the testing capability of the wind tunnel effectively enhanced.
[1]BERTIN J J, CUMMINGS R M.Fifty years of hypersonics: where we've been,where we're going[J].Progress in Aerospace Sciences, 2003, 39(6-7):511-536
[2]BERTIN J J, CUMMINGS R M.Critical hypersonic aerothermodynamic phenomena [J]. Annu Rev Fluid Mech, 2006, 38: 129-157.
[3]FEDOROV A.Transition and stability of high-speed boundary layers [J]. Annual review of fluid mechanics, 2011, 43: 79-95.
[4]MORTENSEN C H, ZHONG X.Real-gas and surface-ablation effects on hypersonic boundary-layer instability over a blunt cone[J].AIAA Journal, 2016, 54(3):980-998
[5]吴正园, 莫凡, 高振勋, 等.湍流边界层与高温气体效应耦合的直接数值模拟[J].空气动力学学报, 2020, 38(6):1111-1119
[6]WU Z Y, MO F, GAO Z X, et al.Direct numerical simulation of turbulent and high-temperature gas effect coupled flow[J].Acta Aerodynamica Sinica, 2020, 38(6):1111-1119
[7]唐志共, 许晓斌, 杨彦广, 等.高超声速风洞气动力试验技术进展[J].航空学报, 2015, 36(1):86-97
[8]TANG Z G, XU X B, YANG Y G, et al.Research progress on hypersonic wind tunnel aerodynamic testing techniques[J].ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1):86-97
[9]尤文佳, 王慧杰, 韩仁坤, 等.高超声速风洞现代试验设计方法研究[J].实验流体力学, 2022, 36(3):20-32
[10]YOU W J, WANG H J, HAN R K, et al.Using modern design of experiments method for hypersonic wind tunnel test[J].Journal of Experiments in Fluid Mechanics, 2022, 36(3):20-32
[11]吴杰.管向超声速流域拓展的设计技术[J].空气动力学学报, 2018, 36(3):480-492
[12]WU J.Extention of hypersonic Ludwieg tube to supersonic wind tunnel[J].Acta Aerodynamica Sinica, 2018, 36(3):480-492
[13]CUMMINGS R, MCLAUGHLIN T.Hypersonic Ludwieg tube design and future usage at the US Air Force Academy[C]//50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2012: 734.
[14]JUHANY K, DARJI A.Force measurement in a Ludwieg tube tunnel[J].Journal of Spacecraft and Rockets, 2007, 44(1):88-93
[15]CASPER M, SCHOLZ P, WINDTE J, et al.Hypersonic PIV in a ludwieg tube wind tunnel at mach 5.9[C]//28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference including the Aerospace T&E Days Forum. 2012: 3197.
[16]HSU P S, JIANG N, JEWELL J S, et al.100-kHz PLEET for hypersonic flow velocity measurements in a Mach 6 Ludwieg Tube[C]//AIAA Scitech 2020 Forum. 2020: 1019.
[17]ODDO R, HILL J L, Reeder M F, et al.Effect of surface cooling on second-mode dominated hypersonic boundary layer transition[J].Experiments in Fluids, 2021, 62(7):144-
[18]张成键, 桂裕腾, 李学良, 等.小攻角下波纹壁对圆锥高超声速边界层稳定性的影响[J].气体物理, 2024, 9(2):66-80
[19]ZHANG C J, GUI Y T, LI X L, et al.Effect of wavy wall on the stability of conical hypersonic boundary layer at small angle of attack[J].Physics of Gases, 2024, 9(2):66-80
[20]李学良, 李创创, 苏伟, 等.分布式粗糙元对高超声速边界层不稳定性的影响试验[J].航空学报, 2024, 45(2):90-108
[21]LI X L, LI C C, SU W, et al.Experiment of influence of distributed roughness elements on hypersonic boundary layer instability[J].Acta Aeronautica et Astronautica Sinica, 2024, 45(2):90-108
[22]张成键, 吕岱霖, 朱畅, 等.HyTRV升力体高超声速边界层稳定性的初步实验研究[J/OL].航空学报, 1-15[2024-06-28].http://kns.cnki.net/kcms/deta il/11.1929.v.20240401.0951.004.html.
[23]ZHANG C J, LV D L, ZHU C, et al.Preliminary experimental study on hypersonic boundary layer stability of HyTRV lift body[J/OL].航空学报, 1-15[2024-06-28].http://kns.cnki.net/kcms/deta il/11. 1929.v.20240401.0951.004.html. (in Chinese).
[24]LI Z Y, XIONG Y D, YUAN X Y, et al.A-variant design of hypersonic Ludwieg tube wind tunnel[J].AIAA Journal, 2022, 60(7):3990-4005
[25]WU J, RADESIPIEL R.Experimental investigation of a newly designed supersonic wind tunnel [J]. Progress in Flight Physics–Volume 7, 2015, 7: 123-144.
[26]WU J, RADESIPIEL R.Damping insert materials for settling chambers of supersonic wind tunnels[J].Experiments in Fluids, 2017, 58(3):19-
[27]WOLF T, ESTORF M, RADESIPIEL R.Investigation of the starting process in a Ludwieg tube [J]. Theoretical and Computational Fluid Dynamics, 2007, 21: 81-98.
[28]WU J, RADESIPIEL R.Tandem nozzle supersonic wind tunnel design[J].International Journal of Engineering Systems Modelling and Simulation, 2013, 5(1-3):8-18
[29]李志远.双喉道气动布局对Ludwieg管风洞的流场影响研究 [D]. 2021. 武汉: 华中科技大学, 2021: 06-01.
[30]LI Z Y.Influence of dual-throat aerodynamic layout on hypersonic Ludwieg tube wind tunnel [D]. Wu Han: Huazhong University of Science and Technology, 2021: 06-01 (in Chinese).
[31]李创创, 李志远, 张振辉, 等.双喉道管风洞启动过程及其有效运行时间延长[J].气体物理, 2024, 9(1):58-69
[32]LI C C, LI Z Y, ZHANG Z H, et al.Starting process of a double-throat Ludwieg tube tunnel and the extension of its effective running time[J].Physics of Gases, 2024, 9(1):58-69
[33]赵家权, 司马学昊, 黄冉冉, 等.一种采用双弯管储气段布局的高超声速管设计[J].空气动力学学报, 2022, 40(4):90-
[34]ZHAO J Q, SIMA X H, HUANG R R, et al.Design of a hypersonic Ludwieg tunnel with a double-bent storage tube[J].Acta Aerodynamica Sinica, 2022, 40(4):90-
[35]黄冉冉, 张成键, 李创创, 等.华中科技大学Φ马赫 管风洞设计与流场初步校测[J].空气动力学学报, 2023, 41(01):39-48
[36]HUANG R R, ZHANG C J, LI C C, et al.Design and preliminary freestream calibration of HUST Φ 05 m Mach 6 Ludwieg tube wind tunnel[J].Acta Aerodynamica Sinica, 2023, 41(1):39-