Abstract
The governing equations for flow inside aero engines and rockets are mainly continuity, momentum, and energy equations. Since flow in both groups of vehicles is compressible, these equations are described only for compressible fluids, namely, air and gases. In addition to these equations, state equation and second law of thermodynamics are added.
Flow through diffuser is considered as it is usually the first module in air-breathing engines. Next, nozzles are also discussed as it is a dominant module in both aero engines and rockets. In both modules, shock waves may be encountered if the flow speed is supersonic. Formation of either oblique or normal shock waves is possible. Thus, the necessary governing equations for isentropic flow in ducts and across shock waves are given. Flow in combustion chambers is also described by Rayleigh flow equations.
Several examples including diffusers and nozzles in aircrafts and rockets, as well as aircraft refueling in air, are discussed.
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El-Sayed, A.F. (2016). A Review of Basic Laws for a Compressible Flow. In: Fundamentals of Aircraft and Rocket Propulsion. Springer, London. https://doi.org/10.1007/978-1-4471-6796-9_2
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DOI: https://doi.org/10.1007/978-1-4471-6796-9_2
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