Jet-type vortex generators impact on take-offand landing characteristics of a wing with slats

Аuthors

Brutyan M. A.^*, Potapchik A. V.^**, Razdobarin A. M.^***, Slitinskaya A. Y.^****

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

*e-mail: m_brut@mail.ru
**e-mail: a.v.potapchik@yandex.ru
***e-mail: razdobarinam@mail.ru
****e-mail: flinas@yandex.ru

Abstract

To increase maximum lifting force coefficient of the aircraft wing with fixed geometry, it is reasonable to use the flow control concept. For this purpose, the new way of flow control about a wing with deflected slat, suggested by authors, is being studied experimentally and numerically. A number of slanting holes (along the flow and longwise a wingspan), through which the air jets are blown-out, is made to create vortex cores at the nose section of the upper surface of the wing’s main part, which opens while the slat root section moving-out. The pilot experimental studies of the new method of the wing with slat flow- around at the take-off and landing modes were performed on a model of a modern long-range aircraft with mechanized wing with moving-out slats and flaps.

The slats are made along the wingspan with a gap along the motor-nacelle pylon. The aircraft model testing while the landing state of the high-lift device with jet-type vortex generators and without them were performed with ADT T-106 TsAGI, equipped with aerodynamic scales. Slats and flaps were in landing state; with corresponding deviation angles of δ_sl = 24° and δ_fl = 36°. Weight measurements of aerodynamic characteristics were performed at the Mach number of the incident flow М_∞ = 0.15. It corresponds to the Reynolds number value of Re = 3.1⋅10⁶ at the pressure pumping up to 5 atm in the working section of the tube. The angle of attack was being changed from 4 to 26°.

Numerical simulations of jet-type vortex generators impact on the wing flow-around pattern in a take-off and landing configuration were performed. Numerical calculations were performed to compare the experiment and the expanded range of the studied parameters. The well-known ANSYS CFX software based on the numerical solution of averaged Navier-Stokes equations for the compressible perfect gas with two-parameter SST turbulence model was used. The flow was considered turbulent starting from leading edge. The surface of the model was assumed adiabatic; the viscosity-temperature relation was determined by Sutherland’s law with the constant C = 110.4 K. The number of computational nodes used for the flow-around modelling with streams increased approximately up to 68 million.

The performed studies of passive technique for streams forming by the air blow-by from low the wing underside to its upside at the numbers of Re = 3.1⋅10⁶ and М_∞ =0.15 revealed the possibility of the maximum lifting force coefficient increase.

Keywords:

flow-around control, jet-type vortex generators, numerical and experimental studies of aerodynamic characteristics

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