Probelm Statement: Compressed air at 40 ∘C and 145 kPa from a large tank is discharged to ambient atmosphere at 101 kPa, through a convergent nozzle of 10 cm2 exit area,Calculate the mass flow rate through the nozzle when the ambient atmosphere is at (a) 101 kPa, (b) 50 kPa, and (c) 30 kPa. Equations […]
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Problem statement:A flow at 60 m s−1 enters a nozzle kept horizontal. The specific enthalpy at the nozzle inlet and exit is 3025 and 2790 kJ kg−1, respectively,Neglecting the heat loss from the nozzle, calculate (a) the flow velocity at the nozzle exit, (b) the mass flow rate through the nozzle, if the inlet area
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problem statement: Helium gas from a storage tank at 1000 kPa and 310 K is flowing out through a convergent nozzle of exit area 3 cm2 to another tank.When the mass flow rate is 0.15 kg s−1, determine the pressure in the second tank. Solution Equations used: 2: Mach Number: 3:Pressure: 4: Isentropic Relations: Isentropic
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The speed of sound (a) is equal to the square root of the ratio of specific heats (g) times the gas constant (R) times the absolute temperature (T). The derivation of this equation is given on a separate page. Notice that the temperature must be specified on an absolute scale (Kelvin or Rankine). calculator developed by- Pawan Indalkar
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The oxidizer mass fraction is a crucial parameter in rocket propulsion systems, determining the proportion of oxidizer to the total propellant mass. To comprehend its significance, consider its impact on rocket performance and efficiency. In this formula: Mass of Oxidizer refers to the mass of the oxidizing agent used in the propulsion system. Total Mass
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A propellant density equation calculator is a tool or program that helps you calculate the density of a propellant based on its mass and volume. The formula used in the calculator is typically: Where: ρ is the density of the propellant in kilograms per cubic meter (kg/m³). m is the mass of the propellant in
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The reaction mass flow rate equation defines the rate at which mass flows through a system during a chemical reaction. It quantifies the amount of reacting material passing through a given area per unit time. Where: m˙r is the reaction mass flow rate (in kg/s), ρ is the density of the reacting fluid (in kg/m³),
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The efficiency of a gas generator cycle can be calculated using the specific impulse equation, which relates the efficiency to the specific impulse and the effective exhaust velocity. The specific impulse is defined as the thrust produced per unit weight flow rate of propellant consumed. It’s expressed as: where Ve is the effective exhaust velocity
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Stagnation pressure, also known as total pressure or pitot pressure, is a thermodynamic property of a fluid flow. It represents the pressure that a fluid would possess if it were brought to rest isentropically (without any losses due to friction or turbulence) from its current velocity. Where: P is the static pressure of the fluid,
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The formula for calculating the divergence angle of a nozzle depends on the specific type of nozzle being used. For a convergent-divergent (CD) nozzle, which is commonly used in rocket propulsion, the divergence angle can be calculated using the following formula: Where: θd is the divergence angle, Me is the exit Mach number of the
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