#engine This program is to calculate performances of rocket engines. I take no responsibility for any damage that is made by this if you use this program.

g : gravity acceleration[m/s^2] R : universal gas constant[J/mol*K] pa : atomospheric pressure[Pa] ita : propulsive efficiency gamma : ratio of specific heat fis : structure mass ratio of refer rhos : dencity of refer To : temperature of atomosphere ml : mass of payload dv : delta v aci : acceleration at initial ts : duration in conbustion chamber i(1) : propellant i(2) : oxygen o(fini) : exhaust gas fini : number of exhaust gas rho?() : dencity of ?() M?() : mass number of ?() h?() : hentalpy of ?() c?() : coefficient in the chemical equation ar : ration of combustion chamber and throat po : pressure of combustion chamber dtank : diameter of tank

ans = payload ratio, pressure of combustion chamber, mixture ratio temperature in combustion chamber specific thrust diameter of combustion chamber length of combustion chamber diameter of tank length of tank