How much propellant would an ideal single stage sugar rocket with dry mass of 1 kg need to reach the altitude of 100 km in a suborbital flight when launched straight up? Let us assume the specific impulse of its motor to be 120 s.
In case more input is needed (rocket diameter etc.) please try to supply some sample numbers. Please also provide the calculation procedure.
PS. Some people are actually trying to do this - they call it Sugar Shot to Space program (SS2S) - just not with "ideal" rocket.