TY - JOUR

T1 - Flow over an aerofoil without and with a leading-edge slat at a transitional Reynolds number

AU - Genc, M S

AU - Kaynak, U

AU - Lock, Gary D

PY - 2009

Y1 - 2009

N2 - In this study, a multi-element aerofoil including NACA2415 aerofoil with NACA22 leading-edge slat is experimentally and computationally investigated at a transitional Reynolds number of 2 x 10(5). In the experiment, the single-element aerofoil experiences a laminar separation bubble, and a maximum lift coefficient of 1.3 at a stall angle of attack of 12 degrees is obtained. This flow has been numerically simulated by FLUENT, employing the recently developed, k-k(L)-omega and k-omega shear-stress transport (SST) transition models. Both transition models are shown to accurately predict the location of the experimentally determined separation bubble. Experimental measurements also illustrate that the leading-edge slat significantly delays the stall up to an angle of attack of 20 degrees, with a maximum lift coefficient of 1.9. The fluid dynamics governing this improvement is the elimination of the separation bubble by the injection of high momentum fluid through the slat over the main aerofoil - an efficient means of flow control. Numerical simulations using k-k(L)-omega are shown to accurately predict the lift curve, including stall, but not the complete elimination of the separation bubble. Conversely, the lift curve prediction using the k-omega SST transition model is less successful, but the separation bubble is shown to fully vanish in agreement with the experiment.

AB - In this study, a multi-element aerofoil including NACA2415 aerofoil with NACA22 leading-edge slat is experimentally and computationally investigated at a transitional Reynolds number of 2 x 10(5). In the experiment, the single-element aerofoil experiences a laminar separation bubble, and a maximum lift coefficient of 1.3 at a stall angle of attack of 12 degrees is obtained. This flow has been numerically simulated by FLUENT, employing the recently developed, k-k(L)-omega and k-omega shear-stress transport (SST) transition models. Both transition models are shown to accurately predict the location of the experimentally determined separation bubble. Experimental measurements also illustrate that the leading-edge slat significantly delays the stall up to an angle of attack of 20 degrees, with a maximum lift coefficient of 1.9. The fluid dynamics governing this improvement is the elimination of the separation bubble by the injection of high momentum fluid through the slat over the main aerofoil - an efficient means of flow control. Numerical simulations using k-k(L)-omega are shown to accurately predict the lift curve, including stall, but not the complete elimination of the separation bubble. Conversely, the lift curve prediction using the k-omega SST transition model is less successful, but the separation bubble is shown to fully vanish in agreement with the experiment.

KW - flow separation control

KW - leading-edge slat

KW - separation bubble

KW - transition models

KW - wind tunnel

UR - http://www.scopus.com/inward/record.url?scp=69249134645&partnerID=8YFLogxK

UR - http://dx.doi.org/10.1243/09544100JAERO434

U2 - 10.1243/09544100JAERO434

DO - 10.1243/09544100JAERO434

M3 - Article

VL - 223

SP - 217

EP - 231

JO - Proceedings of the Institution of Mechanical Engineers Part G - Journal of Aerospace Engineering

JF - Proceedings of the Institution of Mechanical Engineers Part G - Journal of Aerospace Engineering

SN - 0954-4100

IS - G3

ER -