this method matches very well with those obtained using the weigh tloss method. Fig. 9 show slower regression rate up to certain value of Gox to therigh to fline YY. There ason for this is that the pressure is lower atthestart of the combustion process. In order to get properreg ression rate trend line ,the points Gox to the right of line YY have been removed.It is redrawn as shown in Fig. 10. The oxidizer mass flux exponent, n, is also indicated in Fig. 10 for the various experiments .It expresses the dependence of regression rate(_r) in hybrid rocket on the oxidizer mass flux (Gox) through the relation _r ¼ aGnox (a is an empirical constant).