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The fuel regression rate equation and the relation between fuel regression rate and axial distance have been derived.
Fuel regression rate in hybrid rockets is non-negligibly affected by the oxidizer injection pattern.
Other additives, such as metal hydrides, aluminium and boron generally offer improvements on the regression rate.
The fuel regression rate formulas of different fuel components are fitted according to the experiment data.
However, the metal additives in the HTPB fuel can increase the fuel regression rate significantly.
An increased viscosity has been shown to reduce the regression rate of liquefying fuels.
Second, the timing of the follow-up evaluation remains unclear as tumor regression rate varies.
The regression rate of the burning surface along the laminar interface, determined experimentally, is also used as an input.
A correlation is shown between this transition and the optimal thickness that maximizes regression rate (at a given pressure).
The results show that the surface regression rate is transient, decreasing significantly in the leading section and increasing slowly downstream.
The practical implementation of hybrid rocket motors has historically been hampered by the slow regression rate of the solid fuel.
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