Volume 37 Issue 6
Dec.  2023
Turn off MathJax
Article Contents
YANG Y, QIAN F X, ZHANG C F, et al. Research on wind tunnel test technology of sonic boom measurement based on probe[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 92-100 doi: 10.11729/syltlx20210193
Citation: YANG Y, QIAN F X, ZHANG C F, et al. Research on wind tunnel test technology of sonic boom measurement based on probe[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 92-100 doi: 10.11729/syltlx20210193

Research on wind tunnel test technology of sonic boom measurement based on probe

doi: 10.11729/syltlx20210193
  • Received Date: 2021-12-24
  • Accepted Date: 2022-02-24
  • Rev Recd Date: 2022-02-24
  • Available Online: 2024-01-11
  • Publish Date: 2023-12-30
  • Wind tunnel test is an indispensable technical means to carry out sonic boom research. Accurately obtaining sonic boom signals with weak signal attributes from complex wind tunnel test environment is the key of wind tunnel test technology. In order to study the influence of the test environment on the accurate measurement of sonic boom signal in the transient supersonic wind tunnel, a small transient trans-supersonic wind tunnel was used to develop a test device with a needle probe with the characteristics of minimizing interference. A dual motion test system with independent motion of probe and model was established, and the sonic boom measurement technology based on probe was developed. Taking a typical cone-cylinder model as the research object, the differences of the complete sonic boom signals obtained by the two test methods of fixed probe and moving model and fixed model and moving probe are compared, and the sonic boom propagation law of cone-cylinder model and the influence of wind tunnel background flow field on sonic boom measurement are studied. The results show that: Compared with the two test methods of fixed model and moving probe, the former will cause the distortion of sonic boom signal, which leads to more serious distortion of sonic boom signal, while the latter is smoother and more accurate, which is a relatively more reliable test method; The background flow field distribution in wind tunnel has a significant influence on sonic boom signal measurement. It is necessary to master the background flow field distribution in wind tunnel in detail and keep it stable as much as possible. On this basis, the positions of model and probe in wind tunnel and the relative positions of model and probe should be strictly selected.
  • loading
  • [1]
    CANDEL S. Concorde and the future of supersonic transport[J]. Journal of Propulsion and Power, 2004, 20(1): 59–68. doi: 10.2514/1.9180
    [2]
    LEATHERWOOD J D, SULLIVAN B M, SHEPHERD K P, et al. Summary of recent NASA studies of human response to sonic booms[J]. The Journal of the Acoustical Society of America, 2002, 111: 586–598. doi: 10.1121/1.1371767
    [3]
    朱自强, 吴宗成, 陈迎春. 民机空气动力设计先进技术[M]. 上海: 上海交通大学出版社, 2013.

    ZHU Z Q, WU Z C, CHEN Y C. Advanced technology of aerodynamic design for commercial aircraft[M]. Shanghai: Shanghai Jiao Tong University Press, 2013.
    [4]
    朱自强, 兰世隆. 超声速民机和降低音爆研究[J]. 航空学报, 2015, 36(8): 2507–2528.

    ZHU Z Q, LAN S L. Study of supersonic commercial transport and reduction of sonic boom[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(8): 2507–2528.
    [5]
    CARLSON H W. Correlation of sonic-Boom theory with wind-tunnel and flight measurements[R]. NASA TRR–213, 1964.
    [6]
    MENDOZA J P, HICKS R M. Further studies of the extrapolation of near-field overpressure data[R]. NASA TM X–2219, 1971.
    [7]
    HUNTON L W, HICKS, R M, MENDOZA J P. Some effects of wing planform on sonic boom[R]. NASA TND–7160, 1 973.
    [8]
    CARLSON H, MORRIS O. Wind-tunnel sonic-boom testing techniques[C]//Proc of the 2nd Aerodynamic Testing Conference. 1966.
    [9]
    CARLSON H W, MACK R J, MORRIS O A. A wind-tunnel investigation of the effect of body shape on sonic-boom pressure distributions[R]. NASA TND−3106, 1965.
    [10]
    CARLSON H W, MACK R J. A study of the sonic-boom characteristics of a blunt body at a Mach number of 4.14[R]. NASA TP−1015, 1977.
    [11]
    MACK R J, KUHN N. Determination of extrapolation distance with measured pressure signatures from two low-boom models[R]. NASA TM-2004-213264, 2004.
    [12]
    WILCOX F J, ELMILIGUI A, WAYMAN T R, et al. Experimental sonic boom measurements on a Mach 1.6 cruise low-boom configuration[R]. NASA TM-2012-217598, 2012.
    [13]
    MAKINO Y, SUZUKI K, NOGUCHI M, et al. Non-axisymmetrical fuselage shape modification for drag reduction of a low sonic-boom Airplane[R]. AIAA−2003−557, 2003.
    [14]
    FURUKAWA T, MAKINO Y, NOGUCHI M, et al. Supporting system study of wind-tunnel models for validation of aft-sonic-boom shaping design[R]. AIAA−2008−6596, 2008.
    [15]
    DURSTON D A, CLIFF S E, WAYMAN T R, et al. Near field sonic boom test on two low-boom configurations using multiple measurement techniques at NASA Ames[R]. AIAA-2011–3333, 2011.
    [16]
    CLIFF S, ELMILIGUI A, AFTOSMIS M, et al. Design and evaluation of a pressure rail for sonic boom measurements in wind tunnels[C]// Proc of Seventh International Conference on Computational Fluid Dynamics(ICCFD7). 2012.
    [17]
    MORGENSTERN J M. How to accurately measure low sonic boom or model surface pressure in supersonic wind tunnel[R]. AIAA-2012-3215, 2012.
    [18]
    刘中臣, 钱战森, 冷岩, 等. 声爆近场空间压力风洞测量技术[J]. 航空学报, 2020, 41(4): 109–121.

    LIU Z C, QIAN Z S, LENG Y, et al. Wind tunnel measurement techniques for sonic boom near-field pressure[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(4): 109–121.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Figures(17)  / Tables(2)

    Article Metrics

    Article views (66) PDF downloads(7) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return