AirDensity=0.0228645 * baro/(0.5555* (temp - 32) + 273.15) AeroDragFactor = 1.07556 * AirDensity * cd * farea RollingDragFactor = (C1 + C2 * mph2.5) C1 = 0.034667 * (tpress - 35.000000)*(tpress - 45.000000) + -0.063333 * (tpress - 20.000000)*(tpress - 45.000000) + 0.032000 * (tpress - 20.000000)*(tpress - 35.000000); C2 = 7.704e-07 * (tpress - 35.000000)*(tpress - 45.000000) + -8.33333e-07 * (tpress - 20.000000)*(tpress - 45.000000) + 3.148e-07 * (tpress - 20.000000)*(tpress - 35.000000); AeroHP = (AeroDragFactor * mph3)/375.0 RollHP = RollingDragFactor * (weight/1000.) * (mph/375.0) Lift = 0.00256 * farea * clift * mph2