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Prandtl Lifting Line Theory

This script file generates the Lifting Line Theory curve and also return the 3D CL (coefficient of lift) for the wing

The complete step-by-step explanation/docs can be found here (https://geoffreynyaga.com/python-code-lifting-line-theory/)

Setup

  • clone the project
git clone https://github.com/geoffreynyaga/lifting-line-theory.git
  • cd into the project
cd lifting-line-theory
  • create a virtual environment (for Mac/Linux users. Fow windows users create the virtualenv and manually cd into venv/Scripts folder and run activate.bat)
virtualenv venv && source venv/bin/activate
  • install dependancies
pip install -r requirements.txt
  • Replace the following values with your appropriate values
S: float = 24.39  # wing area m^2
AR: float = 7.8  # Aspect ratio
taper: float = 0.45  # Taper ratio
alpha_twist: float = -2.0  # Twist angle (deg)
i_w: float = 1.0  # wing setting angle (deg)
a_2d: float = 6.8754  # lift curve slope (1/rad)
alpha_0: float = -4.2  # zero-lift angle of attack (deg)
  • run the file in Terminal

Results

Screenshot 1

and you also get the resulting CL

0.4049012444698557 CL_wing