On aerodynamics specifics of a small-sized aircraft of normal configuration


Аuthors

Voronich I. V.1*, Kolchev S. A.2**, Panchuk D. V.3***, Pesetsky V. A.4****, Silkin A. A.5*****, Tkachenko V. V.6******, Nguyen T. T.6*******

1. Institution of Russian Academy of Sciences Dorodnicyn Computing Centre of RAS, 40, Vavilov st., Moscow, 119333, Russia
2. Kompani «INREA», 39-1, Kronshtadtsky blv., Moscow, 125499, Russia
3. Kompani «Kronshtadt», 54-4, Malyi ave., Saint-Petersburg, 199178, Russia
4. Central Aerohydrodynamic Institute named after N.E. Zhukovsky, TsAGI, 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia
5. Scientific center of applied electrodynamics», 26, Rizhsky ave., Saint-Petersburg, 190103, Russia
6. Moscow Institute of Physics and Technology, 9, Institutskiy per., Dolgoprudny, Moscow region, 141701, Russia

*e-mail: i.voronich@yandex.ru
**e-mail: sakolchev@gmail.com
***e-mail: uas-1@mail.ru
****e-mail: pesetskiyva@gmail.com
*****e-mail: silkin-a-a@yandex.ru
******e-mail: vtkachenko52@yandex.ru
*******e-mail: thanhtung.tccn@gmail.com

Abstract

The article presents the results of experimental and computational studies of the model flow-around of a small-sized aircraft of normal scheme in the range of Reynolds numbers of Rе = 2÷8 х 105. Experimental studies were performed in the T-102 TsAGI wind tunnel on the full model and the “fuselage-wing” combination both with and without accounting for horizontal and vertical empennage. The tests were conducted at flow rates of 10÷55 m/s, and the turbulence intensity of the incoming flow was about 0.4% at the speeds of 20 m/s and higher. With this, the range of angles of attack was α = -5÷40° for forward and reverse runs, and the range of slip angles was β = -20÷20°. Special attention is being paid to the efficiency of aerodynamic controls. Basic model has the maximum lift coefficient is Cya max = 1.2 at α = 10÷12°; drag coefficient at zero lift is Cxa0≅0.017; maximum aerodynamic quality Kmax ≅ 21 at Cya≅0.5. The computational study was conducted based on Reynolds-averaged Navier-Stokes equations with closure by turbulence model SST + γ — Reθ. In the described conditions at cruise angles of attack, the laminar-turbulent transition on the wing occurs in the form of laminar separation on the upper surface followed by turbulent reattachment (“laminar bubble”). The Reynolds number affects significantly on the flow at supercritical angles of attack, i.e. with the Re increase, the lift and drag increase along with critical angle of attack. On the most part of the wing the effects of three-dimensionality are weak due to the small sweep. The computed flow fields also revealed the presence of the resource for the model aerodynamic characteristics improving. While computing and experiment, satisfactory agreement was reached on the basic characteristics of the complete configuration for the subcritical angles of attack.

Keywords:

aerodynamics, small-sized aircraft, flow field, laminar-turbulent transition

References

  1. Svishchev G.P. Aviatsiya: Entsiklopediya (Aviation: encyclopedia), Moscow, Bol’shaya Rossiiskaya entsiklopediya, 1994, 736 p.

  2. Brusov V.S., Petruchik V.P., Morozov N.I. Aerodinamika i dinamika poleta malorazmernykh bespilotnykh letatel’nykh apparatov (Aerodynamics and flight dynamics of small-sized unmanned aerial vehicles), Moscow, MAI-Print, 2010, 340 p.

  3. Oettershagen P. et al. Perpetual flight with a small solar-powered UAV: Flight results, performance analysis and model validation, 2016 IEEE Aerospace Conference, Big Sky, 2016. DOI: 10.1109/AERO.2016.7500855

  4. Bravo-Mosquera P.D., Botero-Bolivar L., Acevedo-Giraldo D., Ceron-Munoz H.D. Aerodynamic design analysis of a UAV for superficial research of volcanic environments, Aerospace Science and Technology, 2017, vol. 70, pp. 600 – 614.

  5. Selig M.S. Summary of low speed airfoil data, Virginia Beach, SoarTech Publications, 1995, 317 p.

  6. Voronich I.V., Kolchev S.A., Kon’shin V.N., Tkachenko V.V. Aerospace MAI Journal, 2010, vol. 17, no. 5, pp. 24 – 33.

  7. Voronich I.V., Kolchev S.A., Kon’shin V.N., Panchuk D.V., Pesetskii V.A., Tkachenko V.V. Materialy XXII nauchno-tekhnicheskoi konferentsii po aerodinamike TsAGI, Zhukovskii, Tsentral’nyi aerogidrodinamicheskii institut imeni prof. N.E. Zhukovskogo, 2011, pp. 44 – 45.

  8. Voronich I.V., Kolchev S.A., Kon’shin V.N., Panchuk D.V., Pesetskii V.A., Tkachenko V.V. Materialy XXIII nauchno-tekhnicheskoi konferentsii po aerodinamike TsAGI, Zhukovskii, Tsentral’nyi aerogidrodinamicheskii institut imeni prof. N.E. Zhukovskogo, 2012, pp. 69 – 70.

  9. Parkhaev E.S., Semenchikov N.V. Trudy MAI, 2015, no. 80, URL: http://trudymai.ru/eng/published.php?ID=56884

  10. Parkhaev E.S., Semenchikov N.V. Aerospace MAI Journal, 2018, vol. 25, no. 3, pp. 7 – 16.

  11. Aerodinamicheskaya truba T-102: http://www.tsagi.ru/experimental_base/aerodinamicheskaya-truba-t-102

  12. Langtry R.B., Menter F.R. Correlation-Based Transition Modeling for Unstructured Parallelized Computational Fluid Dynamics Codes, AIAA Journal, 2009, vol. 47, no. 12, pp. 2894 – 2906.

  13. Kravets A.S. Kharakteristiki aviatsionnykh profilei (Aviation profiles characteristics), Moscow, Oborongiz, 1939, 332 p.

  14. Pesetskii V.A. et al. Tekhnika vozdushnogo flota, 2004, vol. LXXVIII, no. 1, pp. 20 – 24.

  15. Ermakov V.A. et al. Patent na poleznuyu model’ № 42502 RU, 10.12.2004.

  16. Stepanov R.P., Kusyumov A.N., Mikhailov S.A., Tarasov N.N. Trudy MAI, 2019, no. 107, URL: http://trudymai.ru/eng/published.php?ID=107894

  17. Gorev V.N., Popov S.A., Kozlov V.V. Trudy MAI, 2011, no. 46, URL: http://trudymai.ru/eng/published.php?ID=26026

  18. Kryukov A.V. Uluchshenie aerodinamicheskikh kharakteristik malorazmernogo letatel’nogo apparata putem primeneniya volnistoi poverkhnosti (Aerodynamic characteristics improvement of a small-sized aircraft by wavy surface application). Abstract of the thesis, Novosibirsk, ITPM SO RAN, 2012, 15 p.

  19. Kryvokhatko I.S., Sukhov V.V. Experimental investigation of aerodynamic performance of a small UAV with a telescopic wing, 2013 IEEE 2nd International Conference Actual Problems of Unmanned Air Vehicles Developments Proceedings (APUAVD), Kiev, 2013, pp. 17 – 20.

  20. Rodrigue H., Cho S., Han M.W. et al. Effect of twist morphing wing segment on aerodynamic performance of UAV, Journal of Mechanical Science and Technology, 2016, vol. 30, no. 1, pp. 229 — 236.


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