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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– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This formula calculates the wall temperature of a hypersonic vehicle based on the freestream velocity and temperature. It is crucial for determining thermal loads and designing the thermal protection systems required for vehicles moving at hypersonic speeds. Symbols: Tw​: Wall temperature (K) Te​: Freestream temperature
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– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This formula calculates the boundary layer thickness in hypersonic flows. The boundary layer is a thin layer of air near the surface of a vehicle where the flow velocity changes from zero to the freestream velocity. Understanding boundary layer thickness is critical for predicting drag
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– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This formula calculates the ratio of specific heat in hypersonic flows. The specific heat ratio is a key parameter in a compressible flow, influencing shock wave behaviour and thermodynamic properties of gases at high speeds. Symbols: γ: Ratio of specific heats (dimensionless) Cp​: Specific heat
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– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This formula calculates the dynamic pressure in a hypersonic flow. Dynamic pressure is a key parameter in determining the aerodynamic forces on a body moving through a fluid, especially at high Mach numbers. Symbols: q1​: Dynamic pressure γ: Ratio of specific heats (dimensionless) p1​: Freestream
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– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This formula calculates the Stanton number in hypersonic flows, which is a measure of the heat transfer rate relative to the convective heat transport. It is a critical parameter in analysing thermal protection systems for hypersonic vehicles. Ch​: Stanton number (dimensionless) qw: Heat flux at
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– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This formula calculates the heat transfer rate to a surface in hypersonic flows, which is essential for understanding thermal loads on the surfaces of high-speed vehicles. High-speed flows generate significant heat due to air compression, and this equation helps in managing thermal protection. Symbols: q:
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– Hypersonic and High-Temperature Gas Dynamics, John D. Anderson, Jr. This calculator evaluates the deflection angle for Prandtl-Meyer expansion waves in hypersonic flows. It uses an approximate relation, which becomes more accurate as the Mach numbers (M1 and M2​) increase. The formula helps determine the change in the direction of flow due to expansion, which is
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