Application specifics of tangential jet blow-out on the aircraft wing surface in icing conditions

Aeronautical and Space-Rocket Engineering

Aerodynamics and heat-exchange processes in flying vehicles


DOI: 10.34759/vst-2020-2-7-15

Аuthors

Pavlenko O. V.*, Pigusov E. A.**

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: olga.v.pavlenko@yandex.ru
**e-mail: evgeniy.pigusov@tsagi.ru

Abstract

Icing is one of the most dangerous environmental impacts on an aircraft. Ice bodies on the wing surfaces and empennage change their shape and contours, worsen aerodynamic characteristics, as well as increase aircraft weight. In case of icing not only the aircraft drag increases but the value of the maximum lift coefficient significantly decreases. Various anti-icing systems are employed to remove the ice that builds up in flight. However, practically all these systems have their drawbacks. Application of the wing boundary layer control (BLC) by tangential air jet blow-out on the wing upper surface is known to be one of the most effective techniques for the wing lifting properties at the takeoff-landing modes. The wing lifting properties enhancement occurs due to elimination of the flow separation on the deflected flap by the tangential blow-out of the compressed air jet and flow circulation enhancement on the wing. The hot compressed air for the BLC is drawn from the engine and then piped to the slot nozzles system to be blown-out on the wing surface.

These pipelines are similar to those of the thermal ice-protection system, usually placed along the leading edge of the wing. Thus, the BLC can be employed also to protect against the wing icing. A significant drawback of the above said technical solutions is the jet blowing slot location in an ice sticking area. It is assumed that the hot air from the engine would melt this ice at a certain time instant, but until this moment, the aerodynamic characteristics of the aircraft will degrade. In addition, water evolved while the ice melting on the leading edge, flowing down along the flow is stiffens again out of the BLC coverage forming the so-called “barrier ice”, which also deteriorates the aircraft characteristics. The presented article explores the possibility of the tangential jet blow-out on the leading edge of the wing section to reduce deleterious effect of icing. Calculations were performed employing the program based on numerical solution of Reynolds–averaged Navier-Stokes equations. A case with the horn-like ice on the wing leading edge was under consideration. Comparison of the obtained results with experimental data was performed. The article emonstrates that tangential jet blow-out under of icing conditions allows restoring aerodynamic characteristics level to prior-to-icing state, including coefficients of lift and pitching moment. Specifics of spatial flow-around of the wing section in icing conditions when employing tangential jet blowing-out are presented.

Keywords:

aircraft icing, leading edge icing, horn-like ice imitator, wing lift force, tangential jet blowing-out, wing boundary layer control, anti-icing aircraft system

References

  1. Meshcheryakova T.P. Proektirovanie sistem zashchity samoletov i vertoletov (Aircraft and helicopter protection systems design), Moscow, Mashinostroenie, 1977, 232 p.

  2. Aircraft Icing Handbook. Civil Aviation Authority, 2000, 97 p.

  3. Ice Accretion Simulation. AGARD-AR-344, 1997, 280 p.

  4. Obert E. Aerodynamic Design of Transport Aircraft. Delft University of Technology, IOS Press, 2009, 656 p.

  5. Byushgens G.S. (ed.) Aerodinamika i dinamika poleta magistral’nykh samoletov (Aerodynamics and flight dynamics of mainline aircraft), Moscow -Pekin, TsAGI – Avia-Izdatelstvo KNR, 1995, 765 p.

  6. Teneshev R.Kh., Stroganov B.A., Savin V.S. et al. Protivoobledenitel’nye sistemy letatel’nykh apparatov (Aircraft anti-icing systems), Moscow, Mashinostroenie, 1967, pp. 3, 25, 27.

  7. Apenkina E.A., Dimich V.V., Kretov A.S. Materialy Mezhdunarodnoi molodezhnoi nauchnoi konferentsii (Kazan, 19–21 November 2013) “XXI Tupolevskie chteniya (shkola molodykh uchenykh)”, Kazan, Kazanskii gosudarstvennyi tekhnicheskii universitet, 2013, vol. 1, pp. 11-12.

  8. Polonskii A.P., Fedotova A.S. Materialy VII Vserossiiskoi nauchno-prakticheskoi konferentsii (Irkutsk, 13-16 April 2016) “Aviamashinostroenie i transport Sibiri”, Irkutsk, Irkutskii natsional’nyi issledovatel’skii tekhnicheskii universitet, 2016, pp. 162-166.

  9. Reznikov S.B., Averin S.V., Kharchenko I.A., Tret’yak V.I., Konyakhin S.F. Multiphase pulse transducer for aircraft anti-ice vibrator feeding. Aerospace MAI Journal, 2015, vol. 22, no. 3, pp. 139-145.

  10. Asmakovskii V.Yu. Materialy Mezhdunarodnoi nauchno-prakticheskoi konferentsii (Moscow, 05-08 December 2018) “Klyuchevye trendy v kompozitakh: Nauka i tekhnologii”, Moscow, Diona, 2019, pp. 52-55.

  11. Ezrokhi Yu.A., Kadzharduzov P.A. Working process mathematical modelling of aircraft gas turbine engine in condition of elements icing of its air-gas channel. Aerospace MAI Journal, 2019, vol. 26, no. 4, pp. 123-133. DOI: 10.34759/vst-2019-4-123-133

  12. Brutyan M.A., Potapchik A.V., Razdobarin A.M., Slitinskaya A.Yu. Jet-type vortex generators impact on take-off and landing characteristics of a wing with slats. Aerospace MAI Journal, 2019, vol. 26, no. 1, pp. 19-26.

  13. Petrov A.V. Energeticheskie metody uvelicheniyapod”emnoi sily kryla (Energy methods for increasing the wing lift), Moscow, Fizmatlit, 2011, 402 p.

  14. Petrov A.V. Aerodinamika transportnykh samoletov korotkogo vzleta i posadki s energeticheskimi sistemami uvelicheniya pod”emnoi sily (Aerodynamics of transport aircraft for short take-off and landing with energy systems for lift increasing), Moscow, Innovatsionnoe mashinostroenie, 2018, 735 p.

  15. Pavlenko O.V., Petrov A.V., Pigusov E.A. Materialy XXVIII Nauchno-tekhnicheskoi konferentsii po aerodinamike (p. Volodarskogo, 20-21 April 2017), Zhukovskii, TsAGI, 2017, p. 186.

  16. Pavlenko O.V., Petrov A.V., Pigusov E.A. Materialy XVII Mezhdunarodnoi shkoly-seminara (Evpatoriya, 4–11 June 2017) “Modeli i metody aerodinamiki”, Zhukovskii, TsAGI, 2017, pp. 123-125.

  17. Pavlenko O., Petrov A., Pigusov E. Concept of medium twin-engine STOL transport airplane. 31st Congress of the International Council of the Aeronautical Sciences ICAS-2018 (Belo Horizonte, Brazil, 09-14 September 2018). ICAS2018-0104, 9 p.

  18. Runnels J.N. Boundary layer control and anti-icing apparatus for an aircraft wing. Patent US 3917193A, 04.11.1975.

  19. Swanson E.W., Wehrman M.D. Boundary layer control system for aircraft. Patent US 4099691, 11.07.1978.

  20. Pavlenko O.V. Tekhnika Vozdushnogo Flota, 2006, no. 3-4, pp. 47-51.

  21. Pavlenko O.V. Uchenye zapiski TsAGI, 2009, vol. XL, no. 2, pp. 61-65.

  22. Pavlenko O.V. Uchenye zapiski TsAGI, 2016, vol. XLVII, no. 1, pp. 62–68.

  23. Shih T.H., Liou W.W., Shabbir A., Yang Z., Zhu J. A new k- ε eddy viscosity model for high reynolds number turbulent flows. Computers & Fluids, 1995, vol. 24, no. 3, pp. 227-238. DOI: 10.1016/0045-7930(94)00032-T

  24. Wolfshtein M. The velocity and temperature distribution in one-dimensional flow with turbulence augmentation and pressure gradient. International Journal of Heat and Mass Transfer, 1969, vol. 12, no. 3, pp. 301-318. DOI: 10.1016/0017-9310(69)90012-X

  25. Tran P., Brahimi M.T., Paraschivoiu I., Pueyo A., Tezok F. Ice accretion on aircraft wings with thermodynamic effects. Journal of Aircraft, 1995, vol. 32, no. 2, pp. 444-452. DOI: 10.2514/3.46737

  26. Mingione G., Brandi V. Ice Accretion Prediction on Multielement Airfoils, Journal of Aircraft, 1998, vol. 35, no. 2, pp. 240–246.

  27. Alekseenko S.V., Prikhod’ko A.A. Izvestiya Rossiiskoi akademii nauk. Mekhanika zhidkosti i gaza, 2014, no. 6, pp. 17-36.

  28. Veillard X., Habashi W.G., Aubé M.S., Baruzzi G.S. FENSAP-ICE: Ice Accretion in Multi-stage Jet Engines. 19th AIAA Computational Fluid Dynamics (San Antonio, Texas, 22-25 June 2009). AIAA 2009-4158. DOI: 10.2514/6.2009-4158

  29. Habashi W., Aubé M., Baruzzi G., Morency F., Tran P. FENSAP-ICE: a fully-3D in-flight icing simulation system for aircraft, rotorcraft and UAVS. 24th International Congress of the Aeronautical Sciences, 2004.

  30. Pavlenko O.V., Pigusov E.A. Avtomatizatsiya. Sovremennye tekhnologii, 2018, vol. 72, no. 4, pp. 166–171.

  31. Pavlenko O.V., Pigusov E.A. Numerical investigation of the aerodynamic loads and hinge moments of the flap with boundary layer control. AIP Conference Proceedings, 2018, vol. 1959, no. 1, 050024. DOI: 10.1063/1.5034652

  32. Lawford J.A., Foster D.N. Low-Speed Wind-Tunnel Tests on a Wing Section with Plain Leading- and Trailing-Edge Flaps having Boundary-Layer Control by Blowing. London, Her Majesty’s Stationery Office, 1969. Reports and Memoranda No. 3639.

  33. Starikov Yu.N., Kovrizhnykh E.N. Osnovy aerodinamiki letatel’nogo apparata (Fundamentals of aircraft aerodynamics), Ulyanovsk, UVAU GA, 2004, p. 7.

mai.ru — informational site of MAI

Copyright © 1994-2024 by MAI