I have a conceptual idea for a thruster for a VTOL aircraft/drone which should produce lift by utilizing a upward-flowing airflow to produce low air pressure over the top surface of an airfoil that is embedded within a vertical pipe.
I would like to be able to calculate what the drop in air pressure will be, but being that I am neither an aerospace or aeronautical engineer, I do not know which aerodynamic equation to use to determine this.
I have made some CAD drawings of this conceptual VTOL aircraft/drone thruster to help illustrate and explain how the thruster should produce lift/thrust. (Note: The embedded airfoil is fastened to the vertical pipe with screws and it is colored orange to make it stand out from the rest of the thruster.)
I am thinking of using a Drag Equation that I found on a NASA website to calculate the drop in air pressure, but I'm not sure if it is the right one to use. Reference https://www.grc.nasa.gov/www/k-12/airplane/drageq.html
So, my question is what aerodynamic equation should be used to determine the drop in air pressure over an airfoil embedded within a vertical pipe?