However, for the modified NACA-4415 airfoil, while the hysteresis loop is eliminated, no significant improvement in lift and drag characteristics or stall angles are observed. Additionally, the flow field on the modified airfoil is the same at increasing and decreasing phases of the angles of incidence, ascertaining for the absence of the hysteresis loop in aerodynamic characteristics for all Reynolds number considered here. The velocity field for the modified S1223 airfoil shows attached flow at post-stall angles of attack of the baseline for Reynolds number 100,000 and 150, 000, which results in an improved aerodynamic performance by the modified airfoil. research work, a number of high lift airfoils suited for low Reynolds number regime and high lift capacity like. At Re=200,000, for the modified Selig airfoil, the elimination of hysteresis loop is observed without much decrease in the lift or increase in the drag penalty. Experimental data of a subsonic wind tunnel investigation is. Additionally, the modified airfoil eliminated the hysteresis loop at Re=150,000. In folded state the wingspan is reduced by 50 with a 40 reduction in surface area, and the aspect ratio decreases from 2.9 to 1.2. The tubercles on the S1223 airfoil resulted in a delayed stall, increased lift and decreased drag at Reynolds number of 100,000 and 150,000 when compared to the baseline. To model a NACA 4412airfoil and S1223 airfoils. OBJECTIVE The purpose of this study was to conduct computational fluid dynamics analysis of NACA 4412 and S1223 airfoils with below mentioned objectives. INTRODUCTION An aircraft acted upon by four aerodynamic forces Thrust, Drag, Lift and Weight. S1223 is an airfoil used in heavy lift cargo planes 2. Key words: CFD, Lift, Drag, Pitching, Lift-to-Drag ratio. Velocity flow fields over both airfoils are measured using 2D-particle image velocimetry at selected angles of attack. The S1223 RTL airfoil has been chosen as the most suitable design for the specified boundary conditions and the Mach number from 0.10 to 0.30. Aerodynamic characteristics are measured using a force balance for angles of attack ranging from -6 deg to 24 deg. The tests are conducted at Reynolds numbers of 100,000, 150,000 and 200,000. The influence of airfoil geometry on the effectiveness of tubercles and their ability to improve aerodynamic performance is investigated using flow field and force measurements. An experimental investigation is carried out to study the influence of leading-edge undulations (tubercles) on Selig S1223 (S1223) and NACA-4415 airfoils at low Reynolds numbers.
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