Abstract: The three-dimensional compressible boundary layer flow for a general fuselage with suction is investigated computationally by means of the boundary layer equation for a nonorthogonal curvilinear coordinate system. The stream function is modified and the nonlinear interaction between the boundary condition and the unknown variables is removed through the translation from wall normal velocity to a adjustable parameter of the governing equation. In this paper a numerical technology of crosswise marching along divided segments is developed. It can be used to compute the complicated boundary layer flow in which the sign of the crosswise velocity is changed for many times. Several different suction distributions are designed and their effects on kinds of parameters of boundary layer are investigated. The results show that the effect of suction is obvious and the appropriate suction distribution can appreciably reduce the drag of fuselage.

Key words: boundary layer control, fuselage, three dimension, compressible flow, nonorthogonal curvilinear coordinate system