1.

Specific impluse of a rocket and the critical temperature of the fuel reacted in the motor of the rocket has the relationship

Answer»

`I_(s) prop sqrt((1//T_(c)))`
`I_(s) prop 1//T_(c)`
`I_(s) prop sqrt((T_(c)))`
`I_(s) prop T_(c)`

SOLUTION :The energy of propellant is measurement in terms of a specific impulse INSIDE the motor of the ROCKET. It depend upon the flame temperature and average molecular mass of the gaseous products coming OT of the rocket nozzle. The specific impulse is given by the following relationship with the average molecular mass M and the flame temperature T, `I_(s) = sqrt(T_(c)//M)`.


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