Using the interior-point and axis-point routines developed in the previous assignment, write a program to analyze the oweld in the throat region of an axisymmetric nozzle with Rc = 2.0 and y: 1.4. Analyze the oweld between the straight, vertical initial value line A-B given below and the right-running characteristic AC emanating from the wall. Use 8 = 10'4 as the convergence criterion on the calculated variables, and monitor and print the number of iterations required for each solution point. Right-running characteristic 1. V. line Region to be analyzed Once you have obtained the method of characteristics solution for this region, plot the characteristics net to a suitably large scale in order to see the actual distribution of gridpoints. Also, plot the distributions of Mach number and static-to-stagnation pressure ratio along the nozzle centerline B-C and along the characteristic A-C in the solution region (plot vs. x). [Put both M distributions on one plot and both P/Po distributions on another.] Briey discuss the physical features of the oweld and the numerical features of the solution. Initial value data from the transonic series solution: y = 1.40 R. 2 2.00 7; : 1.00 0.2500 0.0000 1.0423 0.000013+00 0.2500 0.0500 1.0427 1.3706303 0.2500 0.1000 1.0440 2.7895303 0.2500 0.1500 1.0462 4.3060303 0.2500 0.2000 1.0492 5.9724303 0.2500 0.2500 1.0531 7.8452303 0.2500 0.3000 1.0580 9.9868303 0.2500 0.3500 1.0638 1.2468302 0.2500 0.4000 1.0707 1.5371302 0.2500 0.4500 1.0786 1.8790302 0.2500 0.5000 1.0878 2.2840302 0.2500 0.5500 1.0982 2.7654302 0.2500 0.6000 1.1100 3.3395302 0.2500 0.6500 1.1233 4.0259E-02