Volume 34 Issue 6
Dec.  2020
Turn off MathJax
Article Contents
Abstract
References
HE Xuzhao, ZHOU Zheng, ZHANG Juntao, HE Yuanyuan, WU Yingchuan. Mass flux measurement and comparison study of simulation and experiment on curved cone waverider forebody inlet[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(6): 18-23. DOI: 10.11729/syltlx20190095
Citation: HE Xuzhao, ZHOU Zheng, ZHANG Juntao, HE Yuanyuan, WU Yingchuan. Mass flux measurement and comparison study of simulation and experiment on curved cone waverider forebody inlet[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(6): 18-23. DOI: 10.11729/syltlx20190095
shu

Mass flux measurement and comparison study of simulation and experiment on curved cone waverider forebody inlet

  • Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

More Information
  • Received Date: August 01, 2019
  • Revised Date: February 09, 2020
    Graphical Abstract
    • Abstract
  • The mass flow capture performance is a key characteristic of the integrated Curved Cone Waverider forebody Inlet(CCWI). Delicate mass flow measurement experiment and comparison studies between experiment and simulation are conducted for obtaining the CCWI's mass flow capture ratio. Using the mass flow measurement experimental system, the CCWI's mass flow capture and static pressure distribution are obtained at free stream flow Mach number(Ma∞)3.0, 3.5 and 4.0, Angle of Attack (AOA) from -4° to 6°。Comparison studies of CFD simulation and experiment are carried out at Ma∞=4.0, AOA from -4° to 6°。Based on the verified CFD software and simulation methods, the mass flux and compression performance of the CCWI are examined at Ma∞=4.0 and 6.0. The results show that the average square error of the mass flux measurement is less than 2%. Simulation and experimental results agree well with each other. The CCWI has good flow compression abilities and its mass capture ratios are 0.60, 0.68 and 1.00 at Ma∞=3.5, 4.0 and 6.0, AOA=0° respectively.
    • FullText(HTML)
    • References (23)
  • [1]
    MUTZMAN R. MURPHY S. X-51 development: a chief engineer's perspective[C]//Proc of the 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. 2011.
    [2]
    KVCHEMANN D. The aerodynamic design of aircraft[M]. Oxford:Pergamon Press, 1978.
    [3]
    HANEY J W, BEAULIEU W D. Waverider inlet integration issues[R]. AIAA-1994-0383, 1994.
    [4]
    HEISER W H, PRATT D T, DALEY D, et al. Hypersonic airbreathing propulsion[M]. Washington, DC:AIAA Inc., 1994.
    [5]
    BERENS T M, BISSINGER N C. Forebody precompression effects and inlet entry conditions for hypersonic vehicles[J]. Journal of Spacecraft and Rockets, 1998, 35(1):30-36. DOI: 10.2514/3.26994
    [6]
    BILLIG F S, BAURLE R A, TAM C J, et al. Design and analysis of streamline traced hypersonic inlets[R]. AIAA-1999-4974, 1999.
    [7]
    SMART M K. Design of three-dimensional hypersonic inlets with rectangular-to-elliptical shape transition[J]. Journal of Propulsion and Power, 1999, 15(3):408-416. DOI: 10.2514/2.5459
    [8]
    O'NEILL M K L, LEWIST M J. Optimized scramjet integration on a waverider[J]. Journal of Aircraft, 1992, 29(6):1114-1123. DOI: 10.2514/3.56866
    [9]
    TAKASHIMA N, LEWIS M J. Engine-airframe integration on osculating cone waverider-based vehicle designs[R]. AIAA-1996-2551, 1996.
    [10]
    O'BRIEN T F, LEWIS M J. Rocket-based combined-cycle engine integration on an osculating cone waverider vehicle[J]. Journal of Aircraft, 2001, 38(6):1117-1123. DOI: 10.2514/2.2880
    [11]
    SOBIECZKY H, DOUGHERTY F C, JONES K. Hypersonic waverider design from given shock waves[C]//Proc of the 1st International Hypersonic Waverider Symposium. 1990.
    [12]
    STARKEY R P, LEWIS M J. Design of an engine-airframe integrated hypersonic missile within fixed box constraints[R]. AIAA-1999-0509, 1999.
    [13]
    SHUKLA V, GELSEY A, SCHWABACHER M, et al. Automated design optimization for the P2 and P8 hypersonic inlets[J]. Journal of Aircraft, 1997, 34(2):228-235. DOI: 10.2514/2.2161
    [14]
    YOU Y C, ZHU C X, GUO J L. Dual waverider concept for the integration of hypersonic inward-turning inlet and airframe forebody[R]. AIAA-2009-7421, 2009.
    [15]
    LI Y Q, AN P, PAN C J, et al. Integration methodology for waverider-derived hypersonic inlet and vehicle forebody[R]. AIAA-2014-3229, 2014.
    [16]
    贺旭照, 周正, 倪鸿礼.密切内锥乘波前体进气道一体化设计和性能分析[J].推进技术, 2012, 33(4):510-515. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201204004.htm

    HE X Z, ZHOU Z, NI H L.Integrated design methods and performance analyses of Osculating Inward turning Cone Waverider forebody Inlet(OICWI)[J]. Journal of Propulsion Technology, 2012, 33(4):510-515. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201204004.htm
    [17]
    HE X Z, LE J L, ZHOU Z, et al. Osculating Inward turning Cone Waverider/Inlet (OICWI) design methods and experimen-tal study[R]. AIAA-2012-5810, 2012.
    [18]
    周正, 贺旭照, 卫锋, 等.密切曲内锥乘波前体进气道低马赫数性能试验研究[J].推进技术, 2016, 37(8):1455-1460. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201608007.htm

    ZHOU Z, HE X Z, WEI F, et al. Experimental studies of Osculating Inward turning Cone Waverider forebody Inlet(OICWI) at low Mach number conditions[J]. Journal of Propulsion Technology, 2016, 37(8):1455-1460. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201608007.htm
    [19]
    贺旭照, 乐嘉陵.曲外锥乘波体进气道的一体化设计和性能分析[J].推进技术, 2018, 39(10):2313-2319. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201810015.htm

    HE X Z, LE J L. Design and performances analysis of integrated Curved Cone Waverider Inlet[J]. Journal of Propulsion Technology, 2018, 39(10):2313-2319. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201810015.htm
    [20]
    HE X Z, LE J L, WU Y C. Design of a curved cone derived waverider forebody[R]. AIAA-2009-7423, 2009.
    [21]
    贺旭照, 倪鸿礼, 密切曲面锥乘波体——设计方法与性能分析[J].力学学报, 2011, 43(6):1077-1082. https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201106013.htm

    HE X Z, NI H L, Osculating Curved Cone(OCC) waverider:Design method and performance analysis[J]. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(6):1077-1082. https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201106013.htm
    [22]
    TAYLOR T M, VanWie D. Performance analysis of hypersonic shape-changing inlets derived from morphing streamline traced flowpaths[R]. AIAA-2008-2635, 2008.
    [23]
    贺旭照, 赵慧勇, 乐嘉陵.考虑可压缩与热传导的壁面函数边界条件及其应用[J].空气动力学学报, 2006, 24(4):450-453. DOI: 10.3969/j.issn.0258-1825.2006.04.010

    HE X Z, ZHAO H Y, LE J L. Application of wall function boundary condition considering heat transfer and compressibility[J]. Acta Aerodynamica Sinica, 2006, 24(4):450-453. DOI: 10.3969/j.issn.0258-1825.2006.04.010
    • Related Articles

  • Cited by

    Periodical cited type(1)

    1. 李强，操小龙. 超声速进气道压力估算方法及验证. 航空工程进展. 2020(06): 894-899 .

    Other cited types(0)

Catalog

    Get Citation
    PDF
    XML

    Article Metrics

    Article views (282) PDF downloads (13) Cited by(1)
    Related

    Submit Article

    Submission Guidelines

    Contact Us

    Qrcode

    Copyright © Editorial Department of Experimental Fluid Mechanics All Rights Reserved京ICP备14006930号-5

    Address: P. O. Box 11-9, 6 South Section of Second Ring Road, Mianyang, Sichuan 621000, China

    Tel: 0816-2463376 Email: syltlx@163.com

    Supported by: Beijing Renhe Information Technology Co., Ltd.  Baidu Analytics

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return
    x Close Forever Close