Author name: Gurupriya Dey Sarkar

The specific impulse is a measure of the efficiency of a rocket engine in converting propellant mass into thrust. For a methane rocket engine, the combustion typically involves methane (CH4​) and oxygen (O2​), producing carbon dioxide (CO2​) and water (H2O) as products. The chemical equation for the combustion of methane is: CH4+2O2→CO2+2H2O The total mass […]

Calculating the specific impulse for a pulsed detonation engine (PDE) is challenging because PDEs operate on a different principle compared to traditional rocket engines. PDEs use detonation waves to compress and ignite the fuel-air mixture periodically, generating thrust. The intermittent nature of detonation cycles makes it less straightforward to apply the traditional specific impulse formula.

Pulsejets rely on periodic combustion pulses rather than continuous combustion, and their operation is typically more complex. Pulsejets generate thrust by creating repeating cycles of intake, compression, combustion, and exhaust. The specific impulse of a pulsejet can be influenced by factors such as the frequency and efficiency of the combustion pulses, the combustion characteristics, and

The specific impulse is a key performance parameter for rocket engines, measuring their efficiency in converting propellant mass into thrust. Nuclear thermal rocket engines use nuclear reactions to heat a propellant, typically hydrogen, to high temperatures and expel it through a rocket nozzle to generate thrust. For nuclear thermal rockets, the primary source of thrust

The specific impulse is a key performance parameter for rocket engines, measuring their efficiency in converting propellant mass into thrust. Ion thruster engines, also known as ion drives or ion propulsion systems, are a type of electric propulsion that uses ions for thrust generation. Specific impulse for ion thrusters is typically much higher than traditional

The specific impulse is a key performance parameter for rocket engines, measuring their efficiency in converting propellant mass into thrust. For hybrid rocket engines, which combine features of both solid and liquid propulsion systems, the specific impulse is influenced by factors such as the specific design and propellant combination. For hybrid rocket engines, the mass

For aerospike engines, the specific impulse is influenced by the engine design, propellant combination, and operational parameters. For aerospike engines, the mass flow rate is influenced by the design of the aerospike nozzle and the flow characteristics of the propellant. It’s important to note that aerospike engines have unique nozzle designs that can provide more

The specific impulse is a performance parameter commonly associated with rocket engines, providing a measure of the efficiency of the engine in converting propellant mass into thrust. It is defined as the total impulse per unit mass of propellant expended and is typically expressed in seconds. For pressure-fed rocket engines, the specific impulse is influenced

Specific impulse is a measure of the efficiency of a propulsion system in converting propellant into thrust. It is defined as the thrust generated per unit of propellant expended and is expressed in seconds. where, Isp​ is the specific impulse of the rocket engine (in seconds, s) F is the Thrust Produced  ṁ is the mass

To calculate the specific impulse for the Rolls-Royce Gnome engine, we need specific information about the engine’s thrust, burn time, and mass of propellant. It is defined as the thrust generated per unit of propellant expended and is expressed in seconds. where, Isp​ is the specific impulse of the rocket engine (in seconds, s) F is the