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Propulsion
Specific Heat Ratio in Rocket Propulsion Formulas
The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume. And is denoted by γ.
Rocket Propulsion formulas that make use of Specific Heat Ratio
f
x
Rocket Exhaust Gas Velocity
Go
f
x
Throat Velocity of Nozzle
Go
f
x
Specific Volume at Throat
Go
f
x
Specific Temperature at Throat
Go
f
x
Characteristics Velocity
Go
f
x
Area Ratio of Nozzles
Go
f
x
Propellant Mass Flow Rate
Go
f
x
Exit Velocity given Mach Number and Exit Temperature
Go
f
x
Rocket Exit Temperature
Go
f
x
Rocket Exit Pressure
Go
f
x
Compressible Area Ratio
Go
f
x
Exit Velocity given Molar Specific Heat Capacity
Go
f
x
Exit Velocity given Molar Mass
Go
f
x
Mass Flow Rate through Engine
Go
FAQ
What is the Specific Heat Ratio?
The specific heat ratio describes the ratio of specific heats of a gas at constant pressure to that at constant volume.
Can the Specific Heat Ratio be negative?
{YesorNo}, the Specific Heat Ratio, measured in {OutputVariableMeasurementName} {CanorCannot} be negative.
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