Experimental, Numerical & Analytical Verification of Boundary Layer Characteristics Over an Airfoil

This study presents an experimental, numerical and theoretical analysis regarding investigation of boundary layer characteristics over NACA-0015 airfoil under various operating conditions. Experimentally calculated boundary layer and velocity profiles proved to be instrumental in predicting aerodynamic forces and validation studies of numerical & turbulence models. This qualitative and quantitative research, followed by a theoretical and experimental validation scheme, contributes significantly to the field of aerodynamics with its applications in various engineering applications, particularly in the design and optimization of aerodynamic systems. Curve fitting technique was employed to develop an empirical relation for a velocity profile and integrated with momentum integral approach to eventually calculate the drag of an airfoil. Experimental, numerical and theoretical results were consistent with each other thereby validating the research methodology. Results were related with the classical Pohl Hausen and Von Karman boundary layer theories which served as the conventional guidelines to investigate the boundary layers characteristics of laminar and turbulent regimes. The efficacy of wind tunnel testing probe for investigating fluid flow dynamics inside a boundary layer along with key limitations encountered during the research has also been explored and commented upon. Physics of flow inside a boundary layer is discussed, analysed and related with various aerodynamic parameters including Reynold’s number, angle of attack, velocity gradients and boundary layer thickness.