This paper proposes numerical analysis methods to simulate the 6 to 7 km/s class aluminum conical shaped charge (CSC), in order to calibrate the wide-range ballistic limit data obtained by the CSC with the solid spherical projectiles' data. Two kinds of numerical methods are demonstrated by performing a number of numerical analyses with a coupled hydrocode: AUTODYN TM -2D for both the non-inhibited and inhibited CSC: one method is a purely numerical approach and the other is a half-numerical approach combined with a jetting theory. The final purpose of the present study is to assess the orbital space debris impact on the spacecraft in the low earth orbit (LEO), so that aluminum should be adopted as a liner, and the inhibitor should be also equipped. Consequently, the jet ought to have a hollow shape and be vaporized partially. The merits and demerits of two methods are investigated through the numerical analyses, especially the limitations of the half-numerical approach will be made clear when we apply it to the inhibited CSC, while the process of jetting and trapping in the inhibited CSC will be successfully demonstrated by the pure-numerical approach.