Java

do not know how to begin and how to add in the equations

Directions Create a class that computes the lift and drag of a rectangular planform wing. Lift can be calculated with the following equation: ift Cl* A 0.5 rho V2 Cl is the lift coefficient; it is dimensionless A is the area of the wing in m rho is the air density, in kg/m3, for the altitude the wing is flying V is the velocity in m/s Drag can be calculated with the following equation: Drag Cd" A" 0.5" rho-v2 Cd is the drag coefficient; it is dimensionless The other variabies are the same as the lift equation. Notes: Cl and Cd vary with the wing angle of attack. rho varies with altitude. A rectangular planform wing is 85% efficient when compared to the optimal elliptical wing