Question

Specific impulse of a rocket engine is defined as

• A. Thrust produced per unit chamber pressure
• B. Thrust produced per unit weight flow rate of propellant
• C. Exhaust velocity divided by mass flow rate
• D. Chamber pressure divided by mass flow rate

Hint:

The specific impulse of a rocket is \[ \boxed{ I_{sp} = \frac{F}{\dot{m}g_0} } \] and is measured in \[ \boxed{\text{seconds (s).}} \]

Answer 1

The Correct Option is B

Step 1: Recall the definition of specific impulse. Specific impulse is the thrust produced per unit weight flow rate of propellant. Mathematically, \[ \boxed{ I_{sp} = \frac{F}{\dot{m}g_0}, } \] where
• \(F\) = thrust,
• \(\dot{m}\) = propellant mass flow rate,
• \(g_0\) = standard acceleration due to gravity.

Step 2: Identify the correct option. Hence, \[ \boxed{ \text{Specific impulse} = \text{Thrust per unit weight flow rate of propellant.} } \] Therefore, \[ \boxed{(B)} \] is the correct answer.