ECOR 2606 Lab Test #1 v1The diagram illustrates a gas flowing through a nozzle. As the cross sectional area of the nozzle gets smaller and smaller, the gas flows faster and faster until, at the choke point, it is flowing at Mach 1 (M= 1). If the Mach number of the flow at some point in the nozzle is known, the cross sectional area at that point can be calculated using the following formula: 12/1221112*MMAAwhere Ais the cross sectional area at the point of interest Mis the Mach number of the flow at this point A* is the cross sectional area at the choke point γis the specific heat ratio for the gas Part I (3 marks): Write a function m-file (area.m) that, given M, A*, and γ(gamma), computes and returns A. The formula is only valid for 0 < M<= 1. If Mis outside of this range your function should generate
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