Fanno Flow is a type of compressible flow where the fluid flows through a constant area duct with friction. It is named after the Italian physicist Gino Fanno, who first described this type of flow in 1932.
The main assumptions made in Fanno Flow include: the fluid is compressible, the flow is steady and one-dimensional, the duct has a constant cross-sectional area, and there is no heat transfer to or from the fluid.
While both Fanno Flow and Rayleigh Flow are types of compressible flow, they differ in the assumptions made about the flow. Fanno Flow assumes a constant area duct with friction, while Rayleigh Flow assumes a variable area duct with no friction.
The Fanno Flow parameter, also known as the Mach number parameter, is a dimensionless quantity that relates the fluid velocity to the speed of sound in the fluid. It is used to determine the behavior of the flow and the critical conditions at which the flow becomes choked.
Fanno Flow is commonly used in the design and analysis of supersonic aircraft engines, gas pipelines, and rocket nozzles. It is also relevant in the study of shock waves and their effects on aerodynamics and heat transfer in high-speed flows.