I have a video on my YouTube channel that computes the area ratio of the normal shock in the diverging section of a converging-diverging (CD) nozzle. At the end of the video, I go through my MATLAB code. Here are the files you need in order to run the code. The main file is called CD_Nozzle_NSN.m. The functions you will need are called ISENTROPIC_FLOW.m, NORMAL_SHOCK.m, and NS_NOZZLE.m. You can find the isentropic flow function and normal shock function at my GitHub. You can also just download all four files down below.
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I need a solution to following question:
Converging Diverging Nozzle Design You are tasked to design a converging diverging (CD) nozzle for rocket propulsion system. The working fluid is air(k= 1.4). The proposed dimensions of the nozzle are: 1.Inlet radius =0.10 m2.Throat radius =0.075 m3.Outlet radius =0.12 m The rocket is to launch from sea level and fly to an altitude of 100km. The total pressure upstream of the nozzle, P0, inlet= 250 kPa (absolute)for most of rocket trajectory. Between the altitudes of 80kmand 100km the total pressure drops to 0 in a linear fashion. The designed inlet pressure and temperatures areas follows.1.Pinlet= 210 kPa2.T0, inlet= 300 K To verify the design, determine the exit flow conditions at every10km variations in altitude (use reference tables for Pressure and Temperature at various altitudes exit).In case of shock, determine the location of the shock in the CD Nozzle, and propose design alternations to have no shock in CD nozzle through out the length of its planned trajectory.