is there a calculator or spreadsheet on the net to calculate the thrust parameters for a hybrid rocket? I was thinking along the lines of something where you plug in type of fuel, volume of Nox used, combustion chamber size and rate of nox flow.

then after you put this in, it gives you total impulse, average thrust, and other such goodly numbers.

I also would like to know(in hybrids) how one determines chamber pressure, and if one could modify that also.

been lookin at possibly doing a big ex hybrid, and would like to see what size engine woudl be needed. har to tell where to start for weight unless you can get the weight of the casing.