Java: Wing Class Lab

Please elp me finish the remaining requirement of the lab, thank you! I will rate the answer!

I have attached the lab requirment and the code I have below:

public class RectangularWing implements AirDensity { private double span; private double chord; private double vCruise; private double vStall; private double cLiftMax; private double cLiftCruise; private int altitudeTO; private int altitudeCruise; public RectangularWing(double s, double c,double vC,double vS, double cLmax, double cLcruise, int altTO, int altC) { span = s; chord = c; vCruise = vC * 1.689; vStall = vS * 1.689; cLiftMax = cLmax; cLiftCruise = cLcruise; altitudeTO = altTO; altitudeCruise = altC; } public double q(int mode) { double rho = 0; double v = 0; if (mode == TAKEOFF) { rho = AIR_DENSITY[altitudeTO]; v = vStall*1.3; } else { rho = AIR_DENSITY [altitudeCruise]; v = vCruise; } return 0.5*rho*(v*v); } public static void main(String[] args) { RectangularWing w = new RectangularWing( 30, 4.6, 120, 45,1.4, 0.3, 0,3); System.out.println(w.q(TAKEOFF)); } }

Build and test the Wing class using Java Your class should have the following fields Field NameDescription span chord vCruise vStall cLiftMax cLiftCruise altitudeTO altitudeCruise Cruise altitude index (0-20 Wing span in feet Wing chord in feet Table of standard day, and hot day atmosphere density. In slugs Cruise speed in feet per second (fps). Knots x 1.689 = f Stall speed in fps Maximum lift coefficient. Dimensionless Cruise lift coefficient. Usually found at L/D max in airfoil datasheet. Dimensionless Take off altitude index (0-20 Your class should have the following methods Dynamic Pressure, q Variable Name Description Rho. Density of air at given altitude. Standard or hot da Velocity in fps. Knots x 1.689 fps amic pressure Total Lift (lbs.) Tota!Lift = span * chord * q * CL. Cu is the appropriate lift coefficient. Note that span * chord is wing area Wing Loading (lbs. /square foot) WingLoading = Tota Lift / WingArea