Rocket and Space propulsion Archives

techAir
Find the combustion chamber pressure of a rocket engine using hydrogen and oxygen as propellants, whose mass flow in combustion chamber is \(300\,kg/s\). The temperature of the combustion chamber is \(3500\,K\). Gas flowing into the engine has a ratio of specific heats of \(1.2\) and a molecular weight of \(16\). The rocket nozzle throat area is \(0.25\,m^{2}\).
- rocket engine
- rocket propulsion
on 26th March 2021 in Rocket and Space propulsion.
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Kisan Kumar
Find the final burnout velocity of a two-stage rocket which has a payload mass of 100 kg. Specific impulse of both the stages is 290s. First stage gets separated from the second stage at the instant of burnout. Rocket has the following design characteristics:
on 1st March 2021 in Rocket and Space propulsion.
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Worldtech
For a rocket, find the ratio of its propellant mass to the initial mass for which burnout velocity of the rocket is equal to the escape velocity from earth.
on 1st March 2021 in Rocket and Space propulsion.
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techAir
Find the burnout velocity of a rocket with Hydrogen-Fluorine as the fuel oxidizer combination.
on 1st March 2021 in Rocket and Space propulsion.
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Kumar59
Find the thrust produced by a rocket engine at an altitude of \(55\, km\), if the exit area of the rocket engine is \(2.5\,m^2\). Mass flow of the propellants is \(30\,kg/s\) and has a exit velocity of \(4500\,m/s\) and a exit pressure of \(2.2 \times {10^4}\,N/m^2\).
on 12th February 2021 in Rocket and Space propulsion.
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Worldtech
What is a rocket?
on 5th June 2020 in Rocket and Space propulsion.
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Kisan Kumar
A rocket engine is tested on a test bed under the ideal condition of fully expended jet. The exhaust velocity is \(2\; km/s\) through a nozzle of area \(2.5\;m^{2}\). The mass flow rate is \(200 \;kg/s\). What is the specific impulse of the propellant and the thrust developed?
- GATE
on 11th October 2019 in Rocket and Space propulsion.
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Kisan Kumar
Poll How multi staging in rockets improves the burn-out performance ?
- GATE
on 9th October 2019 in Rocket and Space propulsion.
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Kisan Kumar
A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and ratio of specific heats 1.2.The universal gas constant is 8314 J/kg-mol-K. What is the value of theoretical \(c^{*}\) in (m/s)?
- GATE
- rocket propulsion
on 30th September 2019 in Rocket and Space propulsion.
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Poll How multi staging in rockets improves the burn-out performance ?