In this study, the idea of using a cylindrical protuberance installed on spiked - blunt nose is introduced in order to control the aerodynamic coefficients at the hypersonic regim. The problem is modeled using numerical solutions of 3D form of the Navier-Stokes equations. Then, the results are compared with some previous numerical and experimental studies in order to verify them. Furthermore, the effects of several parameters including the location and the height of the protuberance and the free stream Mach number are examined on the flow filed, the aerodynamic coefficients and the aerodynamic heat flux. The results indicate that the lift and moment coefficients can be effectively controlled by the protuberance. Moreover, the results demonstrate that the nose shoulder is the best place for the protuberance installation. In this case, not only the lift and moment coefficients are greater than the other cases but also the drag coefficient increments are less than the others. Also, it can be observed that the lift and moment coefficients are increased by the ratio of the protuberance height to the nose diameter (H⁄D). For example, the lift and pitching moment coefficients at H⁄D=0.3 and Mach number of 5.75 are respectively increased about 140 and 60 percent in comparison with H⁄D=0.1. Also, it can be observed that the heat flux is increased with the height of the protuberance.