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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– 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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– D. Raymer – Aircraft Design. A Conceptual Approach (1992) Wf​: Weight of the fuel required for the mission. Wo​: Initial takeoff weight of the aircraft. Wx​: Weight of the aircraft after completing the mission (excluding fuel weight). The factor 1.06 accounts for a typical 6% reserve and trapped fuel allowance.
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