Gain insights into using Python for mechanical and aerospace engineering. Learn about basics, graphing techniques, airfoil plotting, and dynamic pressure and orbital modeling in 2D and 3D.

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Python tkinter

Python bash

Python pweave

In this course, you will learn about the Python programming language in the context of mechanical and aerospace engineering. 

You will start with the basics of Python, like variables, collections, and different types of loops. Once you have the basics out of the way, the real fun begins. You will learn how to: graph thrust available and thrust required, graph dynamic pressure during a rocket launch, and how to plot airfoil coordinates. 

Towards the end, you will get a strong overview of orbital parameters and learn how to model both 2D and 3D static orbits. Once you’ve completed this course, you will have a better understanding of Python and how it works in the context of mechanical/aerospace engineering.

Python for Mechanical and Aerospace Engineering

Let's talk about importing libraries in Python. You do not need them for this Educative course, but it is another good thing to know!

```python
from numpy import pi
import matplotlib.pyplot as plt
```

Since you do not need the entire `Numpy` library, you can import specific parts of it with the `from x import y` syntax. Calling the `Matplotlib` object `plt` is a common convention, but Python supports any naming convention as long as you are consistent.

The first function will convert knots (kts) to feet per second (fps). Fps is the base unit for velocity in US Imperial units, but most aircraft use knots for velocity. You will show the x-axis of the graph in knots and dynamically calculate the thrust in converting knots to fps.


def knots_to_ftpersec(speed):  
# speed is the user input and is in knots 
    return speed * 1.68781

x = knots_to_ftpersec(100.0)
print('100.0 knots is {} fps'.format(x))

The second function takes density, velocity, wing area, zero-lift drag coefficient Cd0, drag constant K, and aircraft weight and returns the thrust required in lbs. The equation itself is derived from the fact that drag equals thrust at altitude and refactors the drag equation into separate parts. Here is the equation:

$$C_L = \frac{2*\text{Weight}}{\rho_\infty * V_\infty^2 * S}$$

In Python:

Develop a graph for thrust required and thrust available at sea level.

Getting Comfortable with Python

FizzBuzz

Graphing Thrust Available and Thrust Required

Graphing Dynamic Pressure During a Rocket Launch

Getting and Plotting Airfoil Coordinates

Modeling a 2-Body Orbit in 2D and 3D

Unit Conversions

Introduction to Web Scraping

Modeling Camera Shutter Effect

Writing Reports with Pweave

The End

Thrust Available and Thrust Required at Sea Level