Assume you are designing the inlet for a new supersonic aircraft. As a baseline, you need to showthe stagnation pressure that is loss using a normal shock diffuser for M=2 to M=4 (using incrementsof 0.05). Show these results on a plot. Now, I want you to show the results of a double obliqueshock diffuser (for the same range of Mach numbers) that has an initial wedge of 8o, but the secondturn angle can vary; however, the flow cannot be turned by a total of more than 20o. Based on theseresults, describe and draw a figure that shows the “optimal” double oblique shock diffuser youdesigned. Explain your rationale in a short paragraph – make sure to site specific equations, laws,concepts, etc.