This repository contains data on the propulsive parameters of hybrid rocket motors. Data is sourced from the corresponding study [1], in which computational simulations using the software CEA-NASA were carried out. The fuels paraffin wax, hydroxyl-terminated polybutadiene (HTPB) and polymethyl methacrylate (PMMA) were combined with three oxidizers: liquid oxygen (LOX), nitrous oxide (N2O) and hydrogen peroxide (H2O2). The examined propulsive parameters are the characteristic velocity, specific impulse and adiabatic flame temperature. The propellant pair paraffin-LOX provided the highest performance for all parameters studied. These data and constructed relations of the propulsive parameters vs oxidizer-to-fuel ratio can be used in the design of a static test bench and a hybrid propulsion system.

Source:

[1] Mariana Conti Tarifa, Loreto Pizzuti. THEORETICAL PERFORMANCE ANALYSIS OF HYBRID ROCKET PROPELLANTS AIMING AT THE DESIGN OF A TEST BENCH AND A PROPULSIVE SYSTEM. 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS). 2019, DOI: 10.13009/EUCASS2019-488