The authors have proposed end burning type hybrid rockets. A key point of this idea is that a motor uses cylindrical fuel having many ports in axial direction, in which oxidizer gas flows. Because of difficult requirements to make an end burning type solid fuel grain, i.e., high volumetric filling rate above 0.95 and small port intervals, the end burning hybrid rocket was yet to be achieved. This paper reports results of verification firing tests of an end burning type hybrid rocket being realized for the first time. Recent progress of 3D printers made the production of the fuel grain possible. The results clearly show the initial transient and the steady periods of the end burning mode. It also proves a virtue of no oxidizer to fuel ratio shift during firing. Since the initial transient is a period for the exit end face to attain a steady state shape, an initial end face shape being close to the steady state shape can shorten this period. A firing test with a fuel having tapered ports showed that it attains a steady state in less than 1 second, which is much shorter than a non-tapered case of about 6 seconds.