Specific Volume at Throat evaluator uses Specific Volume = Inlet Volume*((Specific Heat Ratio+1)/2)^(1/(Specific Heat Ratio-1)) to evaluate the Specific Volume, The specific volume at throat of a rocket nozzle represents the volume occupied by a unit mass of propellant at that specific location, this formula provides a simplified relationship between the specific volume at the throat and the specific volume at the nozzle exit, taking into account the properties of the gas and the flow conditions within the rocket nozzle. Specific Volume is denoted by Vt symbol.
How to evaluate Specific Volume at Throat using this online evaluator? To use this online evaluator for Specific Volume at Throat, enter Inlet Volume (V1) & Specific Heat Ratio (γ) and hit the calculate button.