Research on the calculation of pressure loss in continuous transonic wind tunnel
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摘要: 为满足未来先进航空航天型号的发展需求，我国逐步展开了大型跨声速风洞建设工作；由于过去从未开展过大型连续式跨声速风洞建设，建设经验较为有限。连续式风洞压力损失估算及各部段气动参数计算是风洞结构、测控系统和动力系统设计的输入条件；压力损失估算结果的准确性，直接影响了风洞动力系统设计的难度。本文结合经典的压力损失计算方法，针对损失的关键部位，结合CFD数值模拟及缩比部段试验结果进行全面的分析，给出了特殊部段尤其是试验段的损失系数，并通过多次迭代计算的方式，给出了各部段气动性能。最后，将风洞压力损失估算值与某0.6 m量级连续式跨声速风洞试验结果进行对比，估算偏差在7.5%以内。Abstract: In order to meet the demand of the development of advanced aerospace models in the future, the construction of large-scale transonic wind tunnels has been carried out. Since the construction of large-scale continuous transonic wind tunnels has never been carried out in the past, construction experience is limited. The estimation pressure loss of the continuous wind tunnel and the calculation of aerodynamic parameters of various parts are the design input conditions for the wind tunnel structure system, measurement and control system, and power system. The accuracy of pressure loss estimation results directly affects the difficulty of the wind tunnel power system design. Using the classical pressure loss calculation method combined with the CFD numerical simulation, this paper comprehensively analyzes the key parts of the loss and the results of scaled section test, and gives the loss coefficient of the special section, especially that of the test section, more accurately. The iterative calculation method gives the aerodynamic performance of each section accurately. Finally, by comparing the estimated value of the wind tunnel pressure loss with the test results of 0.6 m continuous wind tunnel, the estimated uncertainty is within 7.5%.
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Key words:
- continuous wind tunnel /
- transonic /
- pressure loss /
- experimental verification
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图 9 孔壁试验段简化模型(二维)CFD计算结果
Figure 9. Calculation results of the simplified model (2D) for perforated-wall test section
图 10 Ma=1.00，0.2 m试验段试验结果
Figure 10. The test results of 0.2 m test section at Ma=1.00
图 12 0.2 m试验段试验结果(Ma=1.10)
Figure 12. The test results of 0.2 m test section at Ma=1.10
图 13 低超声速范围支架段马赫数云图
Figure 13. Mach number diagram of model support section with low supersonic range
表 1 边界条件一览表
Table 1. List of boundary conditions
部件名称 边界条件 二维喷管入口 总温、总压、流动方向等 试验段出口 外插 风洞横向中间截面 对称面 计算模型半模分界面 对称面 单槽分界面 欧拉壁面 槽腔壁板 无滑移绝热壁 驻室壁面 无滑移绝热壁 试验段壁板 无滑移绝热壁 二维喷管壁板 无滑移绝热壁 Flap片 无滑移绝热壁 
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表 2 风洞各部段损失系数
Table 2. Loss coefficient of each part of the wind tunnel
部段名称 当地损失系数 部段名称 当地损失系数 第二喉道段 0.0341 大角度扩散段 1.692 再入段 0.0078 风洞冷却器 20 方变圆段 0.018 大角度收缩段 0.05 第一扩散段 0.06 第三拐角段 0.25 第一拐角段 0.24 三、四拐角间等直段 0.012 一、二拐角间等直段 0.8452 第四拐角段 0.25 第二拐角段 0.24 稳定段 4.5 压缩机段 0.25 收缩段 0.34 第二扩散段 0.0685 喷管段 0.028
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Uncertainty of circuit loss predictions Project Method Loss estimation Uncertainty Facility upgr. Analytical Data base sim. tunnels 30%~40% Facility upgr. Semi-emp. Experimental data base < 5%~10% New tunnel Experiment Test-rig high-speed leg < 10%~15% New tunnel Experiment Complete model tunnel < 5%~10% New tunnel Semi-emp. Loss program + test data < 5%~10% New tunnel Semi-emp. Data base sim. tunnels 30%~40% New tunnel Analytical Present 1D method < 10%~15% New tunnel Analytical Numerical(CFD)
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[1] GOETHERT B H. Transonic wind tunnel testing[M]. London:Pergamon Press, 1961. [2] WOLF T. Computation of power requirements for subsonic and transonic wind tunnels[C]//Proc of the 15th Applied Aerodynamics Conference. 1997. [3] ECKERT W T, MORT K W, JOPE J. Aerodynamic design guidelines and computer program for estimation of subsonic wind tunnel performance[R]. NASA-TN-D-8243, 1976. [4] WOLF T. State of the art in circuit loss analysis of transonic wind tunnels[C]//Proc of the 20th AIAA Advanced Measurement and Ground Testing Technology Conference. 1998. [5] DAVIS M W. Optimum transonic wind tunnel[C]//Proc of the AIAA 14th Aerodynamic Testing Conference. 1986. [6] 凌其扬.西北工业大学NF-6风洞气动性能估算[B].西安: 西北工业大学, 1997. [7] 伍荣林, 王振羽.风洞设计原理[M].北京:北京航空学院出版社, 1991.WU R L, WANG Z Y. Wind tunnel design principle[M]. Beijing:Beijing Aeronautical Institute Press, 1991. [8] 华绍曾, 杨学宁.实用流体阻力手册[M].北京:国防工业出版社, 1985.HUA S Z, YANG X N. Applied fluid resistance handbook[M]. Beijing:Defense Industry Press, 1985. [9] 刘政崇, 廖达雄, 董谊信, 等.高低速风洞气动与结构设计[M].北京:国防工业出版社, 1999.LIU Z C, LIAO D X, DONG Y X, et al. Aerodynamic and structure designs of high speed and low speed wind tunnel[M]. Beijing:National Defense Industry Press, 1999. [10] GUNN J A, MARTINDALEW R, Wagner D W. Performance evaluation of a transonic wind tunnel compressor[R]. AIAA 92-3927, 1992. [11] IDELCHIK I E. Handbook of hydraulic resistance[M]. 2nd ed. New York:Hemisphere Publishing, 1986. -
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