A) \[{{I}_{s}}\propto {{T}_{c}}\]
B) \[{{I}_{s}}\propto 1/{{T}_{c}}\]
C) \[{{I}_{s}}\propto \sqrt{\left( {{T}_{c}} \right)}\]
D) \[{{I}_{s}}\propto \sqrt{(1/{{T}_{c}})}\]
Correct Answer: C
Solution :
The energy of propellant is measured in terms of a specific impulse. Is inside the motor of the rocket. It depend up on the flame temperature and average molecular mass of the gaseous products coming out 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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