مطالعه عددی رشد یخ شبنم و روشن روی دهانه بال پهپاد

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشکده مهندسی دانشگاه فردوسی مشهد ، مشهد، ایران

2 دانشکده مهندسی. دانشگاه فردوسی مشهد ، مشهد ، ایران

چکیده

در این پژوهش رشد دو نوع یخ شبنم و روشن در طول دهانه بال یک پهپاد (UAV) مورد مطالعه قرار گرفت. همچنین علت فیزیکی تشکیل این یخ‌ها روی سطح به‌همراه تاثیر یخ‌زدگی روی ضرایب آیرودینامیکی بال توسط روش عددی بررسی شد. برای این‌منظور، بال مستطیلی با مقطع ناکا0012 در زاویه حمله 4 درجه، در دو دمای مختلف مورد مطالعه قرار گرفت. از حلگر فشارمبنا و مدل آشفتگی یک معادله‌ای اسپالارت-آلماراس در نرم افزار تجاری استفاده شد. محاسبات در رینولدز 106×3 صورت گرفت. نتایج حاصل از الگوی رشد یخ حاکی از آن است که روی دهانه بال از ریشه تا میانه تفاوتی میان ضخامت یخ وجود نداشته ولی از قسمت میانه تا نوک، به‌علت افزایش سرعت جریان، میزان برخورد و تجمیع قطرات در ناحیه مذکور افزایش یافته که نتیجه آن افزایش ضخامت یخ می‌باشد. همچنین تحت شرایط یخ روشن، در نزدیک لبه فرار به‌علت رشد لایه مرزی، یخ تشکیل می‌شود. با انجام محاسبات مشابه درحالت غیرلزج و عدم رشد یخ در نزدیک لبه فرار، صحت این ادعا نیز ثابت شد. ازطرفی پدیده جریان القایی که روی نوک بال‌های سه‌بعدی به-وجود می‌آید، باعث برخورد قسمتی‌از قطرات به نوک بیرونی بال و درنتیجه رشد مقداری ناچیز یخ در ناحیه مذکور می‌شود. بعلاوه بررسی ضرایب برآ و پسا نشان داد که تشکیل یخ باعث افت عملکرد آیرودینامیکی بال می‌شود. همچنین این مطالعه نشان داد که افت عملکرد ناشی از یخ روشن به‌دلیل ایجاد شاخ روی سطح بال، بیشتر از یخ شبنم می‌باشد.

کلیدواژه‌ها

عنوان مقاله [English]

Numerical study of glaze and rime ice accretion along UAV’s wing span

نویسندگان [English]

  • Mohammad Hassan Djavareshkian 1
  • Farzan Haghian 2
1 Mech. Engg. Dept. Faculty of Engg. Ferdowsi University of Mashhad
2 Faculty of engineering. Ferdowsi University of Mashhad
چکیده [English]

In this study, the growth of glaze and rime ice along the UAV’s wing span was studied. In addition, the cause of the formation of these ices on the surface and the effect of ice accretion on the aerodynamic performance of the wing were investigated numerically. For this reason, a rectangular wing with NACA 0012 airfoil section at an angle of attack of 4 degree was studied at two different temperatures. A pressure-based solver and the Spalart-Allmaras turbulence model were used in commercial software. Calculations were performed at Re = 3×106. The results of the ice growth pattern indicate that there was no difference between the ice thickness on the wing span from root to middle, but from the middle to the tip, due to the increase in flow velocity, the rate of collision and the accumulation of droplets in the area increased. Also under glaze ice conditions, ice forms near the trailing edge due to the growth of the boundary layer. This calculation also proved the accuracy of this claim by performing similar calculation in the inviscid condition and the lack of ice growth near the trailing edge. On the other hand, the vortex phenomenon that occurs on the tip of the three-dimensional wings causes part of the droplets to hit the tip of the wing, resulting in the growth of a small amount of ice in this area. study of lift and drag coefficients showed that ice formation reduces the aerodynamic performance of the wing. This study also showed that the aerodynamic performance degradation due to glaze ice due to the formation of horns on the wing surface is more than that of rime ice.

کلیدواژه‌ها [English]

  • wing icing
  • aerodynamic performance
  • ice accretion
  • drag coefficient

Smiley face

مراجع

  1. Venkataramani, K., McVey, L., Holm, R., and Montgomery, K. “Inclement weather considerations for aircraft engines”, 45th AIAA Aerospace Sciences Meeting and Exhibit, p. 695, 2007.
  2. Mason, J., Strapp, W., and Chow, P. “The ice particle threat to engines in flight”, 44th AIAA Aerospace Sciences Meeting and Exhibit, p. 206, 2006. Mason, W. Strapp, and P. Chow, "The ice particle threat to engines in flight." p. 206, 2006.
  3. M. Jones, M. S. Reveley, J. K. Evans, and F. A. Barrientos, “Subsonic aircraft safety icing study,” 2008.
  4. -q. Zhao, Q.-j. Zhao, and X. Chen, “New 3-D ice accretion method of hovering rotor including effects of centrifugal force,” Aerospace Science and Technology, vol. 48, pp. 1-130-22, , 2016.
  5. Ilianna,“Experimental Investigation of Droplet Impingement on Dry Solid Surfaces,” UNIVERSITY OF THESSALY, 2020.
  6. ANSYS FENSAP-ICE User Manual, U.S.A, 2017.
  7. P. Raj, J. Lee, and R. Myong, “Ice accretion and aerodynamic effects on a multi-element airfoil under SLD icing conditions,” Aerospace Science and Technology, vol. 85, pp. 320-333, 2019.
  8. Han, J. Palacios, and S. Schmitz, “Scaled ice accretion experiments on a rotating wind turbine blade,” Journal of Wind Engineering and Industrial Aerodynamics, vol. 109, pp. 55-67, 2012.
  9. Hann, "UAV icing: Comparison of LEWICE and FENSAP-ICE for ice accretion and performance degradation." p. 2861, 2018.
  10. Reckzeh, “Aerodynamic design of the high-lift-wing for a Megaliner aircraft,” Aerospace Science and technology, vol. 7, No. 2, pp. 107-119, 2003.
  11. O. Valarezo, F. T. Lynch, and R. J. McGhee, “Aerodynamic performance effects due to small leading-edge ice (roughness) on wings and tails,” Journal of aircraft, vol. 30, No. 6, pp. 807-812, 1993.
  12. ‌ and‌‌ Costes, and F. Moens, “Advanced numerical prediction of iced airfoil aerodynamics,” Aerospace Science and Technology, vol. 91, pp. 186-207, 2019.
  13. and Szilder, and S. McIlwain, In-flight icing of UAVs-the influence of Reynolds number on the ice accretion process, 0148-7191, SAE Technical Paper, 2011.
  14. . Williams, A. Benmeddour, G. Brian, and M. Ol, "The effect of icing on small unmanned aircraft low Reynolds number airfoils." pp. 19-25, 2017.
  15. Doostmahmoudi, M.Mirzaei, and Nazemian alei, Experimental study on flow pattern and aerodynamic coefficients of NLF-0414 iced airfoil, in persian, 2016.

 

  1. Mirzaei, M. A. Ardekani, and M. Doosttalab, “Numerical and experimental study of flow field characteristics of an iced airfoil,” Aerospace Science and Technology, vol. 13, no. 6, pp. 267-276, 2009.
  2. Reid, G. Baruzzi, I. Ozcer, D. Switchenko, and W. Habashi, "FENSAP-ICE simulation of icing on wind turbine blades, part 1: performance degradation." 51st AIAA Aerospace Sciences Meeting and including the New Horizons Forum and Aerospace Exposition, p. 750, 2013.
  3. Fortin and G. Perron, "Wind turbine icing and de-icing." p. 750, 2013. p. 274, 2009.
  4. Jackson, The dynamics of fluidized particles: Cambridge University Press, 2000.
  5. Bourgault, H. Beaugendre, and W. G. Habashi, “Development of a shallow-water icing model in FENSAP-ICE,” Journal of Aircraft, vol. 37, no. 4, pp. 640-646, 2000.
  6. L. Messinger, “Equilibrium temperature of an unheated icing surface as a function of air speed,” Journal of the aeronautical sciences, vol. 20, No. 1, pp. 29-42, 1953.
  7. H. Beaugendre, F. Morency, and W. G. Habashi, “FENSAP-ICE's three-dimensional in-flight ice accretion module: ICE3D,” Journal of aircraft, vol. 40, No. 2, pp. 239-247, 2003.
  8. Beaugendre, F. Morency, and W. G. Habashi, “Development of a second generation in-flight icing simulation code,” 2006.
  9. م. نادری نژاد, و م. ح جوارشکیان, “بررسی عددی تأثیر سه نوع بالک مختلف بر عملکرد آیرودینامیکی جریان در عدد رینولدز پایین,” دوفصلنامه مکانیک سیالات و آیرودینامیک
    ,vol. 9, no. 1, pp. 83-98, 2020.
  10. K. Lynch, “Bio-inspired adaptive wingtip devices for low Reynolds number operation,” 2017.
  11. Shin and T. BOND, "Results of an icing test on a NACA 0012 airfoil in the NASA Lewis icing research tunnel." p. 64, 1992.
  12. Shin, and T. H. Bond, Experimental and computational ice shapes and resulting drag increase for a NACA 0012 airfoil: Citeseer, 1992.

 

فایل ها

سابقه مقاله

  • تاریخ دریافت: 12 آبان 1400
  • تاریخ بازنگری: 26 دی 1400
  • تاریخ پذیرش: 02 بهمن 1400
  • تاریخ انتشار: 01 اسفند 1400

هم رسانی

ارجاع به این مقاله

آمار