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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)?
A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and …
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Kisan Kumar Asked on 30th September 2019 in Rocket and Space propulsion.
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What is a rocket?
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Worldtech Asked on 5th June 2020 in Rocket and Space propulsion.
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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 \(2.2 \times {10^4}\,N/m^2\).
Find the thrust produced by a rocket engine at an altitude of \(55\, km\), if the exit area of the …
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Kumar59 Asked on 12th February 2021 in Rocket and Space propulsion.
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Find the burnout velocity of a rocket with Hydrogen-Fluorine as the fuel oxidizer combination.
Find the burnout velocity of a rocket with Hydrogen-Fluorine as the fuel oxidizer combination. Ratio of initial weight before making …
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techAir Asked on 1st March 2021 in Rocket and Space propulsion.
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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.
For a rocket, find the ratio of its propellant mass to the initial mass for which burnout velocity of the …
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Worldtech Asked on 1st March 2021 in Rocket and Space propulsion.
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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:
Find the final burnout velocity of a two-stage rocket which has a payload mass of 100 kg. Specific impulse of …
rocket engine

rocket facts

rocket propulsion

Kisan Kumar Asked on 1st March 2021 in Rocket and Space propulsion.
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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 \(0.25\,m^{2}\).
Find the combustion chamber pressure of a rocket engine using hydrogen and oxygen as propellants, whose mass flow in combustion …
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rocket propulsion

techAir Asked on 26th March 2021 in Rocket and Space propulsion.
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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)?

What is a rocket?

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 \(2.2 \times {10^4}\,N/m^2\).

Find the burnout velocity of a rocket with Hydrogen-Fluorine as the fuel oxidizer combination.

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.

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:

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