Abstract
The enormous loss of momentum leads to stall and adversely affects the aerodynamic performance of aeroplane wings which may lead to a disaster, more importantly, risking the safety of the aeroplane by putting lives of passengers on it in danger. Therefore, this paper focuses on the enhancement of aerodynamic characteristics of NACA 23012 through the mitigation of flow separation and delay of the stall at higher angles of attack by using suction for Reynolds number (Re) = 3.4 x 106 . Considering the different suction features such as suction width, suction position, and suction coefficient, the separation delay capability of a suction control is studied. Also, the lift to drag ratio and the impact of energy consumption variation during the control technique are used for estimating the control effects. The Reynolds Average Navier-Stokes (RANS) equations are employed together with the Menter’s shear stress turbulent model. The result of this study revealed that the jet position just behind the separation point at 0.2 % of the chord length shows an outstanding control outcome on the separation and stall, thereby increasing the lift. The lift to drag ration increased proportionately when the suction jet coefficient was increased. At suction coefficient Cq = 0.00225, a 92.1% drag reduction and 72.7% lift enhancement is observed. Hence, the stall angle is moved beyond 21.5o from an initial angle of 16° and the more energy was saved at a high angle of attack.
Highlights
The combined effect of adverse pressure gradient and skin friction occur more often at higher angle of attack or low Reynolds numbers, this induces enormous energy loss which results to the drop in the aerodynamic performances of aeroplanes during departure, landing and during manoeuvring of unmanned aerial vehicles (UAV) leading to large loss of momentum over the aerofoil
It shows clearly that at the lower angle of attack ranging from 0o to ~10o, there was no separation and there is a full attachment of flow around the aerofoil
The ANSYS Fluent was used to study the characteristics of the flow past a NACA 23012 aerofoil at Re = 3.4 × 106, angle of attack up to 18°
Summary
The combined effect of adverse pressure gradient and skin friction occur more often at higher angle of attack or low Reynolds numbers, this induces enormous energy loss which results to the drop in the aerodynamic performances of aeroplanes during departure, landing and during manoeuvring of unmanned aerial vehicles (UAV) leading to large loss of momentum over the aerofoil. Owens and Perkins (1996) experimentally worked on the control of separation of the boundary layer on highly swept cranked delta wing via suction Their results showed an increment in the lift to drag ratio to be 21% plus there was an effective enhancement of the aerodynamic characteristic of the wing. Yousefi and Saleh (2015) and Yousefi et al (2013a), (2014b) worked on the numerical optimization of suction parameters on the aerodynamic properties of NACA 0012 They concluded that suction having 0.5 amplitude and located at the leading edge between 1.75 and 12.5% of the chord length improved the aerodynamic properties of the aerofoil. That is, they observed the maximum lift, reduction in drag and stall improvement with these suction parameters. The aerodynamic properties and performance of a NACA 23012 aerofoil, the impact of suction control and its parameters, and the impact of the energy absorbed during the process of control (using the figure of merit (FOM)) are numerically analysed at a Reynolds number of 3.4 × 106
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