Abstract: In the process of aerodynamic design, the panel method is one of the main computing tools. In this paper the second generation low order panel method is used for calculation of the pressure distribution on the nacelle in low speed. It is demonstrated that the present low order method gives comparable accuracy to the result of high order panel method, It is excellent compared with some earlier low order methods, e.g. "the leakage" in internal flows calculation does not appear with the present method. Meanwhile, the computing cost of the method is very low and it is very easy for application to complex configurations.

Key words: panel method, nacelle, incompressible tlow