Description
(please don't use any AI-generator or old solutions)
Give a code and a brief explanation of how you approached and solved the problem.
Reproduced the answer, for example, 11.1, and create a contour similar to Figure 11.14 in the textbook. Also, repeat the process to produce a nozzle with exit Mach number of 3.5
The quasi-one-dimensional theory provides no capability of solving for the contour of a supersonic nozzle. If the nozzle contour is not proper, shock waves may form inside the nozzle. The method of characteristics provides a technique for properly designing the contour of a supersonic nozzle for shock-free, isentropic flow.
1) Reproduce the results in Example 11.1 and create a contour similar to Figure
11.14 in the textbook.
Update:
Part (2) is for extra credit.
2) Create a nozzle contour for an exit Mach number of 3.5.
More increments used in the method, produces a better contour. Example 11.1 uses 6 increments. Try using more if possible. I recommend you attempt Example 11.1 using Excel first to understand the method. Please submit your original work for the assignment. I will be checking if online codes are used. You can use any software or programming languages you like. Submit a brief report presenting your results.
For the throat, use a distance of 0.125 m from the centerline to point (a). You can use the equations below to determine Mach number once 𝜈 is known. Angles are in radians
Explanation & Answer
please view the answer and explanation below.
Method of Characteristics for Supersonic Nozzle Design
Introduction
The method of characteristics is used to design a supersonic nozzle contour that ensures shockfree, isentropic flow.
Methodology
Prandtl-Meyer Function
Calculates the expansion a...
