The equation you provided represents the drag coefficient (CD) of an aircraft in level flight. It is used to calculate the drag coefficient based on the total drag force (Ta) and the dynamic pressure of the airflow over the aircraft’s wings.
Where:
- CD is the drag coefficient (dimensionless).
- Ta is the total drag force acting on the aircraft (in newtons or pounds-force).
- ρ is the air density (in kg/m³ or slugs/ft³) at the current altitude.
- V is the true airspeed of the aircraft (in m/s or ft/s).
- S is the wing area of the aircraft (in square meters or square feet).