علوم و فناوری فضایی

علوم و فناوری فضایی

Boundary Layer Transition and Re-Laminarization in the Nozzle of a Shock Tunnel – a Numerical Study

نوع مقاله : مقالة‌ پژوهشی‌

نویسندگان
1 پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
2 دانشگاه فنی دانمارک، لینگبی، دانمارک
چکیده
The boundary layer behavior in hypersonic nozzle of a shock tunnel has been investigated by means of the computational fluid dynamics simulations. The state of boundary layer at the nozzle outlet can highly affect the downstream flow passing around the test model in the shock tunnel test section. The formation of shock and expansion wave systems towards the downstream diaphragm and the reflection and expansion waves towards the upstream shock tube were well-simulated after the diaphragm rupture. Focusing on the transitional boundary layer simulation, results of the optimal nozzle's steady-state flow indicate that the boundary layer enters the throat region, undergoes a phase transition, and then returns to a laminar state due to re-acceleration. The turbulence intensity in this region, coupled with the width of the transition zone, increases with higher upstream stagnation pressure. Furthermore, simulation of the unsteady starting flow shows that the passage time of unsteady waves and the quasi-steady region, have good agreement with the experimental results.
کلیدواژه‌ها
موضوعات

[1]   I. Kim, S. Lee, G. Park, and J.K. Lee, "Overview of flow diagnosis in a shock tunnel," International Journal of Aeronautical and Space Sciences, vol. 18, no. 3, pp 425-435, 2017, https://doi.org/10.5139/IJASS.2017.18.3.425.
[2]   N. R. Tichenor, “Characterization of the influence of a favorable pressure gradient on the basic structure of a Mach 5.0 high Reynolds number supersonic turbulent boundary layer,” Ph.D. dissertation, Texas A&M University, 2010.
[3]   F. Lu and D. Wilson, “Survey of short duration, hypersonic and hypervelocity facilities,” In 25th Plasmadynamics and Lasers Conference, Springs, CO, U.S.A, 1994, Paper 94-2491, https://doi.org/10.2514/6.1994-2491.
[4]   S. Gu and O. Herbert, “Capabilities and limitations of existing hypersonic facilities,” Progress in Aerospace Sciences, vol. 113, 2020, Art. no. 100607, https://doi.org/10.1016/j.paerosci.2020.100607.
[5]   L. Duan, G. L. Nicholson, J. Huang, K. M. Casper, R. Wagnild, and N. Bitter, "Direct numerical simulation of nozzle-wall pressure fluctuations in a mach 8 wind tunnel." in AIAA Scitech 2019 Forum, San Diego, California, 2019, Paper 0874, https://doi.org/10.2514/6.2019-0874.
[6]   J. C. Ownbey, “Preliminary design of a high-enthalpy hypersonic wind tunnel facility and analysis of flow interactions in a high-speed missile configuration,” M.S. thesis, School of Aeronautics and Astronautics West Lafayette, Indiana, 2021.
[7]   P. Collen et al., “Development and commissioning of the T6 Stalker Tunnel,” Experiments in Fluids, vol. 62, 2021, Art. no. 225, https://doi.org/10.1007/s00348-021-03298-1.
[8]   E. N. Hoffman et al., “Characterization of the UTSA mach 7 ludwieg tube,” in AIAA SciTech 2022 Forum, San Diego, CA & Virtual, 2022, https://doi.org/10.2514/6.2022-1600.
[9] L. H. Back, R. F. Cuffel, and P. F. Massier, “Laminarization of a turbulent boundary layer in nozzle flow—boundary layer and heat transfer measurements with wall cooling,” ASME. Journal of Heat andMass Transfe, vol. 92, no. 3, pp. 333-344, 1970, https://doi.org/10.1115/1.3449668.
[10] J. H. Kemp Jr and F. K. Owen, “Nozzle wall boundary layers at Mach numbers 20 to 47,” AIAA Journal, vol. 10, no. 7, pp. 872-879, 1972, https://doi.org/10.2514/3.50239.
[11] J. P. Kreskovsky, S. J. Shamroth, and H. Mcdonald, “Parametric study of relaminarization of turbulent boundary layers on nozzle walls,” NASA, Tech. Rep. CR-2370, 1974.
[12] T. Jentink, “An evaluation of nozzle relaminarization using Low Reynolds Number k-epsilon turbulence models,” in 31st Aerospace Sciences Meeting, Reno, NV, USA, 1993, https://doi.org/10.2514/6.1993-610 .
[13] J. P. Abraham, E. M. Sparrow, J. C. K. Tong, and D. W. Bettenhausen, “Internal flows which transist from turbulent through intermittent to laminar." International Journal of Thermal Sciences, vol. 49, no. 2, pp. 256-263, 2010, https://doi.org/10.1016/j.ijthermalsci.2009.07.013.
[14] P. Bader, P. Pieringer, and W. Sanz, “On the capability of transition models to predict relaminarization,” in 12th European Conference on Turbomachinery Fluid dynamics & Thermodynamics, Stockholm, Sweden, 2017, Paper ETC2017-328, https://doi.org/10.29008/ETC2017-328.
[15] N.A. Kiselev, N.S. Malastowski, Y.A. Vinogradov, and A.G. Zditovets, “Experimental and numerical study of heat transfer under laminarization condition in a small size supersonic nozzle,” International Journal of Thermal Sciences, vol. 187, 2023, Art. no. 108182, https://doi.org/10.1016/j.ijthermalsci.2023.108182.
[16] S. Malekipour, M. Mohammadi Amin, and I. Bahman Jahromi, “Towards a low noise shock tunnel facility via multi-objective optimization of hypersonic nozzle,” Journal of Aerospace Engineering, vol. 34, no. 5, 2021, https://doi.org/10.1061/(ASCE)AS.1943-5525.0001296.
[17] S. Malekipour, I. Bahman Jahromi, and M. Mohammadi Amin, “Experimental investigation of Mach 6 optimal hypersonic nozzle performance in shock tunnel,” Journal of Aeronautical Engineering, vol. 25, no. 2, pp. 21-33, 2023, https://doi.org/10.22034/joae.2023.366731.1139.
[18] F. R. Menter, R. B. Langtry, S. R. Likki, Y. B. Suzen, P. G. Huang, and S. Völker, “A correlation-based transition model using local variables—part I: Model formulation,” Journal of Turbomachinery, vol. 128, no. 3, pp. 413-422, 2006, https://doi.org/10.1115/1.2184352.
[19] S. Kang, H. C. Shin, S. H. Park, J. Park, and D. Park, “Comparative assessment of modified γ-Re_θt models for scramjet intake flow analysis,” International Journal of Aerospace Engineering, vol. 2021, no. 1, 2021, Art. no. 9916416, https://doi.org/10.1155/2021/9916416.
[20] J. G. Marvin, J. L. Brown, and P. A. Gnoffo, “Experimental database with baseline CFD solutions: 2-D and axisymmetric hypersonic shock-wave/turbulent-boundary-layer interactions,” NASA, Tech. Rep. TM-2013-216604. 2013.
[21] C. Aliaga, K. Guan, J. Selvanayagam, J. Stokes, V. Viti, and F. Menter, “Hypersonic applications of the laminar turbulent transition SST model in ANSYS Fluent,” In AIAA AVIATION 2020 FORUM, Virtual Event, 2020, https://doi.org/10.2514/6.2020-3290.

  • تاریخ دریافت 02 بهمن 1403
  • تاریخ بازنگری 19 بهمن 1403
  • تاریخ پذیرش 28 بهمن 1403
  • تاریخ اولین انتشار 05 اسفند 1403