Design and test of short centerline probe in continuous transonic wind tunnel
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摘要: 为深入研究不同类型短轴探管的测值特性,设计了多种无需张线固定的短轴探管,通过风洞试验开展了相关探索研究。试验结果表明:不同外形参数的短轴探管与长轴探管在马赫数在0.95以下时马赫数方均根偏差量差异不超过0.000 3,马赫数修正量差异不超过0.000 8,测值曲线无明显变化;马赫数在1.0~1.4区间时,不同形式的短轴探管与长轴探管的测试结果存在明显差异,优化短轴探管头部外形参数、增加柱段长度可不同程度地降低头部对试验段流场的干扰。Abstract: Several types of short centerline probes were designed without need of cable fixation.The characteristics of the measured values were studied by wind tunnel test.The results showed that the difference of Mach number root-mean-square deviation between short centerline probe and long centerline probe with different shape parameters was less than 0.000 3,the difference of Mach number correction was less than 0.000 8,and the measurement curve had no obvious change when the Mach number was below 0.95;There were great differences between short centerline probe and long centerline probe of different shape parameters When the Mach number was between 1.0 and 1.4,changing the shape parameters of short centerline probe or increasing probe length can reduce the interference of head to flow field to some extent.
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Key words:
- transonic wind tunnel /
- flow quality /
- short centerline probe /
- configuration design /
- wind tunnel test
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[1] 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,2003:282-283. [2] 恽起麟.实验空气动力学[M].北京:国防工业出版社,1991. [3] JACKSON F M.Calibration of the AEDC-PWT 16-ft transonic tunnel at test section wall porosities of two,four,and six percent[R].AEDC-TR-76-13,1976. [4] REED T D.Calibration of transonic and supersonic wind tunnels[R].NASA-CR-2920,1977. [5] DICK R S.The influence of several cable-type supports upon the static pressures along the centerline tube in a transonic wind tunnel[R].AEDC-TN-54-26,1955. [6] JACKSON F M.Supplemental calibration results for the AEDC propulsion wind tunnel (l6T)[R].AEDC-TR-70-l63,1970. [7] 李峰,高超,张正科,等.NF-6增压连续式跨声速风洞流场特性与标模试验[J].实验流体力学,2013,27(1):61-64. [8] 陈德华,王维新,王晋军,等.2.4 m跨声速风洞流场性能调试研究[J].空气动力学报,2004,22(3):279-282. [9] 陈德华,王瑞波,刘光远,等.2.4 m跨声速风洞槽壁试验段调试及流场校测[J].实验流体力学,2013,27(4):66-70. [10] JACKSON C M,CORLETT W A,MONTA W J.Description and calibration of the Langley unitary plan wind tunnel[R].NASA-TP-1905,1981. [11] KOHZAI M,UENO M,SHIOHARA T,et al.Calibration of the test section Mach number in the JAXA 2 m×2 m transonic wind tunnel[R].AIAA-2008-0848,2008. [12] HUDGGINS M,HERGERT D.Methodology and results from a recent calibration of the boeing transonic wind tunnel[R].AIAA-2005-4280,2005. [13] AMAYA M,FLACH R,L'ESPERANCE A.Initial testing of the Ames unitary short static pipe[R].AIAA-2017-1277,2017. [14] 吴盛豪,斐海涛,陈吉明,等.跨声速风洞中轴探管的应用[J].航空动力学报,2018,33(10):2451-2457. [15] 黎壮声,杨鹏程,陈旦,等.0.6 m连续式跨声速风洞总压控制策略设计[J].实验流体力学,2016,30(4):87-92. [16] 陈旦,张永双,李刚,等.一种连续式跨声速风洞总压控制方法设计[J].实验流体力学,2019,33(6):65-71. [17] 陈旦,杨孝松,李刚,等.连续式风洞总压和调节阀相关性研究及其应用[J].西北工业大学学报,2020,38(2):325-332. [18] 熊波,周恩民,程松,等.0.6 m连续式风洞调试运行关键技术研究[J].实验流体力学,2016,30(4):81-86.
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