Studies of flow-around of high-lift wing airfoil with combined energy system for the wing lifting force increasing

Aeronautical and Space-Rocket Engineering

Aerodynamics and heat-exchange processes in flying vehicles


Аuthors

Pavlenko O. V.*, Petrov A. 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

Commercial air transportation growth and environmental requirements toughening encourage designers of prospective aviation to develop and research innovative technical solutions and technologies to improve performance while conjoined emissions reduction. In recent years, increased attention has been paid to the study of the Distributed Electric Propulsion (DEP) application, which implementation onboard aircraft, according to researchers, will allow fuel costs cutting by more than 50% with conjoined carbon dioxide emissions reduction by approximately 50%. Many scientific and engineering problems should be solved while the aircraft with DER development. One of such problems, to which solution a great number of today’s studies is devoted, consists in ensuring high takeoff-landing performances. The presented work considers the possibility of employing combined lift force increasing power system (CLFIPS) for the wing lift force improving at the takeoff-landing modes. Evaluation of various factors impact, such as the propeller diameter and thrust; its position along the length and height relative to the airfoil chord at various angles of the flap deflection and blowout intensity on it, on the CLFIPS effectiveness. Along with the basic calculation option, the slipstream effect of the propeller on the aerodynamic characteristics of the airfoil with slotted flap, as well as with the system of circulation control by tangential blowout of the jet on the rounded rear edge of the airfoil are considered.

Computational study of the airfoils flow-around by the viscous gas flow was performed at the numbers of M = 0.13 Re = 7.2·106 employing the FLUENT software based on the numerical solution of the Reynolds-averaged Navier–Stokes equations. The blow-off calculations at various values of the propeller active section diameter and its position were performed at the zero angle of attack.

Parametric studies of the high-lift airfoil flow-around were performed at various values of the propeller relative diameter, being modelled by the “active” disk, and its position relative to the airfoil. The studies confirmed the effectiveness of the combined lift force increasing system conjoining boundary layer control (BLC) system and propeller blow-off (PBO), compared to the speed circulation control by tangential blowout of the jet on the rounded rear edge of the airfoil, as well as the blow-off of the airfoil with the Fowler flap type.

It is advisable to go on with the studies on parameters optimization of the combined BLC/PBO system as well as the type and parameters development of the wing slot mechanics, which ensures effective jet deflection from the wing for the purpose of significant lift force increase.

Keywords:

propeller, tangential jet blow-off, power system for lift force increasing, boundary layer control, circulation control

References

  1. NASA. Aeronautics Research: Strategic Implementation Plan. Washington, DC, United States, Technical Reporth, 2017.

  2. AIRBUS S.A.S. Global market forecast: Cities, Airports & Aircraft 2019 – 2038, 2018, https://www.airbus.com/content/dam/corporate-topics/strategy/global-market-forecast/GMF-2019-2038-Airbus-Commercial-Aircraft-book.pdf

  3. BOEING. Commercial market outlook 2019–2038, 2018, https://www.boeing.com/commercial/market/commercial-market-outlook/

  4. Alternative Jet Fuels. Chevron Corporation, 2006, https://www.chevron.com/-/media/chevron/operations/documents/chevron-alternative-jet-fuels.pdf

  5. Chernousov V.I., Krutov A.A., Pigusov E.A. Containerized Air Freight System Powered by Cryogenic Fuel. 31st Congress of the International Council of the Aeronautical Sciences – ICAS’2018 (09-14 September 2018; Belo Horizonte, Brazil).

  6. Bowman C.L., Felder J.L., Marien T.V. Turbo-and hybrid-electried aircraft propulsion concepts for commercial transport. AIAA/IEEE Electric Aircraft Technologies Symposium – EATS’2018 (12-14 July 2018; Cincinnati, OH, United States). AIAA 2018-4984. DOI: 10.2514/6.2018-4984

  7. Kim H.D. Distributed propulsion vehicles. 27th Congress of the International Council of the Aeronautical Sciences (19–24 September 2010; Nice, France). URL: 20100036222.pdf

  8. Stoll A.M., Mikic G.V. Design Studies of Thin-Haul Commuter Aircraft with Distributed Electric Propulsion. 16th AIAA Aviation Technology, Integration, and Operations Conference (13–17 June 2016; Washington, D.C.). AIAA Paper 2016-3765. DOI: 10.2514/6.2016-3765

  9. Moore K.R., Ning A. Distributed Electric Propulsion Effects on Existing Aircraft Through Multidisciplinary Optimization. IAA Structures, Structural Dynamics, and Materials Conference (08–12 January 2018; Kissimmee, Florida, USA). AIAA Paper 2018-1652. DOI: 10.2514/6.2018-1652

  10. Stoll A.M., Bevirt J.B., Moore M.D., Fredericks W.J., Borer N.K. Drag Reduction Through Distributed Electric Propulsion. 14th AIAA Aviation Technology, Integration, and Operations Conference (16–20 June 2014; Atlanta, GA). AIAA Paper 2014-2851. DOI: 10.2514/6.2014-2851

  11. Stoll A.M. Comparison of CFD and Experimental Results of the LEAPTech Distributed Electric Propulsion Blown Wing. Aviation Technology, Integration, and Operations Conference (22–26 June 2015; Dallas, Texas). AIAA Paper 2015-3188. DOI: 10.2514/6.2015-3188

  12. Dunaevskii A.I., Perchenkov E.S., Chernavskih Yu.N. Takeoff-landing characteristics of regional aircraft with auxiliary retractable distributed electric power installation. Aerospace MAI Journal, 2020, vol. 27, no. 1, pp. 19-29. DOI: 10.34759/vst-2020-1-19-29

  13. Dunaevskii A.I., Chernavskikh Yu.N. Materialy XXVIII Nauchno-tekhnicheskoi konferentsii po aerodinamike (20–21 April 2017; p. Volodarskogo). Zhukovskii, TsAGI im. prof. N.E. Zhukovskogo, 2017, p. 120.

  14. Egoshin S.F. Impact evaluation of multi-propeller wing blow-over system on the STOL aircraft characteristics. Aerospace MAI Journal, 2018, vol. 25, no. 4, pp. 64-76.

  15. Petrov A.V. Aerodynamics of STOL airplanes with powered high-lift systems. 28th Congress of the International Council of the Aeronautical Sciences (23-28 September 2012; Brisbane, Australia). ICAS 2012-9.5.2.

  16. Petrov A.V. Aerodinamika transportnykh samoletov korotkogo vzleta i posadki s energeticheskimi sistemami uvelicheniya pod"emnoi sily (Aerodynamics of short take-off and landing transport airplanes with power systems for the lifting force increasing), Moscow, Innovatsionnoe mashinostroenie, 2018, 736 p.

  17. Petrov A.V. Energeticheskie metody uvelicheniya pod«emnoi sily kryla (Energy methods for increasing the wing lift), Moscow, Fizmatlit, 2011, 404 p.

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

  19. Pavlenko O.V., Pigusov E.A. Materialy XVIII Mezhdunarodnoi shkoly-seminara “Modeli i metody aerodinamiki” (04-11 June 2018; Evpatoriya), Zhukovskii, TsAGI, 2018, pp. 113-114.

  20. 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, 1959, p. 050024. DOI: 10.1063/1.5034652

mai.ru — informational site of MAI

Copyright © 1994-2020 by MAI