Boundary layers on aerofoils form due to the no-slip condition in fluid dynamics, where the velocity at the wall is zero, creating a velocity gradient up to the free-stream velocity. This gradient results in a thin layer of slower-moving fluid adjacent to the surface, typically less than half an inch thick at high speeds. For experiments, boundary layer equations for flat plates can be applied, and the Hiemenz stagnation solution can be used at the leading edge of the airfoil. Understanding these principles is crucial for analyzing pressure distribution at various angles of attack. This foundational knowledge is essential for further research on boundary layers in aerodynamics.
