Re Reynolds Number - S Planform Area m2 V∞ Free stream Velocity m/s α Angle of Attack Degrees ε Induced Downwash Angle Degrees μ Dynamic Viscosity kg/m.s ρ Density kg/m3 τ Shear Stress N/m2 (Make alphabetical) Chapter 1: Introduction This final year project focuses on analysing the aerodynamic characteristics of low Mach number airfoil stall on a NACA-0018 airfoil (you didn’t use a – earlier for the NACA 0018, also what does NACA stand for? You should be specific with what aerodynamic characteristics). Airfoil shape, wing planform, wing twist, taper ratio and many others aspects, affect the stall characteristics of a three-dimensional wing (if you are going to mention specific aspects at least say they are the most important). Studying an airfoil’s characteristics is a key step in analysing the overall performance of three-dimensional wing stall (I’m not sure here, why are you mentioning this? Are you using it this characteristics in choosing an airfoil?). Understanding and predicting flow separation is an important tool in wing design. In order to understand and predict flow separation, the key aspects of an airfoil’s performance must be known (what key aspects? You haven’t mentioned any yet…). An important aspect of airfoil performance is the maximum lift coefficient that an airfoil may reach before stall occurs. The stalling speed of an aircraft is determined by the maximum lift coefficient. The lift coefficient varies linearly with angle of attack at low to moderate angles of attack. When a sufficient angle of attack is reached, the flow on the upper surface of the airfoil begins to separate due to viscous effects and the flow within the separated region begins to reverse direction. The viscous effects near the airfoil surface are the cause of flow separation (could remove this). Flow reverses in direction and separates from the surface of an airfoil because the shear stress between the airfoil surface and the
Re Reynolds Number - S Planform Area m2 V∞ Free stream Velocity m/s α Angle of Attack Degrees ε Induced Downwash Angle Degrees μ Dynamic Viscosity kg/m.s ρ Density kg/m3 τ Shear Stress N/m2 (Make alphabetical) Chapter 1: Introduction This final year project focuses on analysing the aerodynamic characteristics of low Mach number airfoil stall on a NACA-0018 airfoil (you didn’t use a – earlier for the NACA 0018, also what does NACA stand for? You should be specific with what aerodynamic characteristics). Airfoil shape, wing planform, wing twist, taper ratio and many others aspects, affect the stall characteristics of a three-dimensional wing (if you are going to mention specific aspects at least say they are the most important). Studying an airfoil’s characteristics is a key step in analysing the overall performance of three-dimensional wing stall (I’m not sure here, why are you mentioning this? Are you using it this characteristics in choosing an airfoil?). Understanding and predicting flow separation is an important tool in wing design. In order to understand and predict flow separation, the key aspects of an airfoil’s performance must be known (what key aspects? You haven’t mentioned any yet…). An important aspect of airfoil performance is the maximum lift coefficient that an airfoil may reach before stall occurs. The stalling speed of an aircraft is determined by the maximum lift coefficient. The lift coefficient varies linearly with angle of attack at low to moderate angles of attack. When a sufficient angle of attack is reached, the flow on the upper surface of the airfoil begins to separate due to viscous effects and the flow within the separated region begins to reverse direction. The viscous effects near the airfoil surface are the cause of flow separation (could remove this). Flow reverses in direction and separates from the surface of an airfoil because the shear stress between the airfoil surface and the
FYP_oisin_reviewed.docx