Hybrid rockets present a compromise between solid and liquid rockets. It has a simpler
design than liquid rockets and higher performance than solid rockets. It is constructed
from an oxidizer tank followed by a solid fuel grain. Therefore, the combustion is
controlled. This paper presents an algorithm to construct the design space of the hybrid rocket motor
for a single cylindrical port. A simple regression rate formula is used to treat the
combustion. The inner diameter of the grain, outer diameter of the grain, and length of
the grain are used as parameters to construct the design space and a single design point is
chosen. The performance of this design point is presented with the combustion time.