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


DOI: 10.34759/trd-2019-109-8

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 (National Research University), 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

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