The low order panel method with Neumann boundary condition have been used to predict the
normal force curve slope, the pitching moment curve slope, the center of pressure location and the
aerodynamic load distribution for missile in compressible, steady flow. The wing-body-canard
interference problem have been solved using two schemes (iterative method and internal singularity
method) both are based on the panel method. The normal force curve slope, the pitching moment
curve slope and the center of pressure location for a given missile has been predicted using the
present numerical method and the DATCOM technique.