Higher order strip integral method for three-dimensional boundary layers

The consideration of the boundary layer over the surface is important in the design of aircraft wings and other similar lifting surfaces. Relatively easy is the calculation of two-dimensional boundary layers, while computation of three-dimensional boundary layers is difficult and time consuming. Integral methods based on parametric representation of velocity profiles can have advantages compared to finite difference methods. However, parametric representation is not always possible. Strip integral methods offer an alternative to solve the problem. Results obtained by the application of the strip integral method area found to be very encouraging. A description is provided of the Higher Order Strip Integral Method (HOSIM), taking into account its application to a case with considerable cross flow. The results obtained by HOSIM are compared to data obtained with the aid of an approach reported by Loos (1955).