By assuming irrotational inviscid flow of a perfect gas moving past slender pointed bodies at supersonic speeds, the limiting values of the aerodynamic force coefficients as the thickness tends to zero are determined for bodies of general cross-section. The expression for the drag coefficient at zero incidence is the same as that for a body of revolution when expressed in terms of the cross-sectional area at any point. The lateral force coefficients and the extra drag coefficient at incidence depend only on the shape of the base section.