Flow Around an Airfoil with a Moving Surface
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Flow Around an Airfoil with a Moving Surface A. M. Gaifullin1* and K. G. Khayrullin1** (Submitted by A. M. Elizarov) 1
Central Institute of Aerohydromechanics (TsAGI), Zhukovskii, Moscow oblast, 140180 Russia Received January 19, 2020; revised February 27, 2020; accepted March 5, 2020
Abstract—The numerical simulation of the flow around the airfoil formed by the moving surface is investigated. The influence of the wall motion into aerodynamic performance of the airfoil is studied in two-dimensional formulation for RANS equations. DOI: 10.1134/S1995080220070148 Keywords and phrases: airfoil, numerical modelling, flow control.
1. INTRODUCTION The development of high-lift airplane wing requires enhancing the airfoil performance which allows to decrease operating costs. The growth of the cruise Mach number or the angle of attack can lead to the flow separation and unsteady interaction between the boundary layer and the shock wave on the suctions side of the wing known as the transonic buffet phenomenon. This can further lead to the structural vibrations. The wing design requirements impose margins between the buffet onset and the cruise condition. A delay in the buffet onset could improve the aerodynamic performance that can result in the reduction of the wing area and hence the friction part of the drag. Methods such as a jet blowing, a boundary layer suction, different types of a vortex generators have been investigated and employed in practice with a varying degree of success. The main objective of these methods is to delay the separation of the boundary layer from the wall. This can be accomplished by effecting the boundary layer with a moving surface. It injects an additional momentum into the flow and prevents a growth of the boundary layer thickness by diminishing a relative motion between the surface and the flow. Newton was the first to observe the effect of rotation on flight trajectory of the spinning ball. Rayleight and Magnus [1] studied the effect of the rotating cylinder in a free stream and noticed a lift. Kalinin and Mazo [2] studied flow around the rotating cylinder and obtained that the flow regime (steady or periodic) depended on the rotation rate and the free stream Reynolds number. Goldstein [3] illustrated the principle of boundary layer control using a rotating cylinder placed at the leading edge of a flat plate. The flow around a flat plate with a moving surface was studied analytically in [4–6]. The most effective practical application of the boundary layer control with the use of partially moving surface of the wing was demonstrated by Favre [7]. A detailed review on the moving wall boundary layer control on subsonic flow regimes was given by Modi [8]. In present work the transonic flow around a supercritical airfoil formed by a moving surface was investigated. The effects of the moving wall on the flow in the boundary layer, on integral and distributed aerodynamic characteristics of the airfoil were considered. * **
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