I've been making a program for my Civil Air Patrol rocketry teacher that will calculate the total altitude of a rocket in both a dragfree and normal enviroment. The drag free code works fine but the normal code (DMotor and DRocket) don't give me good output. Can anyone identify a problem? I'm using VC6 on Windows 98.

THANKSCode:#include <math.h> #include "conversion.h" #define g 9.81 #define p 2.696 #define rho 2.696 #define GRAV 32.2 double sqr(double inp) { return inp*inp; } struct OutputData { double Sb, Sc, St, VMax, VAve; }; struct DOutputData { double yc, y1, yt; }; class DFreeMotor { public: double Weight, TImpulse, TImpP, AveT, MaxWeight; double BurnW, TDur, VMax, VAve, Sb, Sc, St; DFreeMotor() { Weight = 3.12; TImpulse = 2.5; AveT = 8; TDur = 0.32; MaxWeight = 113.2; TImpP = 100; } OutputData OutD; OutputData Calc(double LiftW); }; OutputData DFreeMotor::Calc(double LiftW) { TImpulse *= (TImpP / 100); TImpulse = NSecLBSec(TImpulse); BurnW = LiftW - Weight; BurnW = GramLB(BurnW); TDur = TImpulse / AveT; VMax = TImpulse*GRAV/BurnW; VAve = VMax/2; Sb = VAve * TDur; Sc = sqr(VMax)/(2*GRAV); St = Sb + Sc; OutD.Sb = Sb; OutD.Sc = Sc; OutD.St = St; OutD.VMax = VMax; OutD.VAve = VAve; return OutD; } class DFreeRocket { public: DFreeMotor Engine; double Weight; DFreeRocket() { Weight = 32; } OutputData OutD; OutputData Calc(); }; OutputData DFreeRocket::Calc() { OutD = Engine.Calc(Weight); return OutD; } class DMotor { public: /* Terms: m : Rocket Mass (KG) A : Rocket Cross-Sectional Area in m^2 cd: Drag Coefficient = 0.75 for average rocket t : Burn Time, Thrust Duration T : Average Thrust I : Motor Impulse v : Burnout Velocity y1: Burnout Altitude yc: Coasting Distance ta: Coasting time => Delay Time for Motor mr: Empty Rocket Mass me: Loaded Rocket Mass mp: Propellant Weight */ double m, A, Cd, t, T ,I, v, y1, yc, ta, maxw, mr, me, mp; double k, q, x, qa, qb; DOutputData OutD; DOutputData Calc(double LiftW); DMotor() { mp = 3.12; I = 2.5; T = 8; maxw = 113.2; I = 100; Cd = 0.75; } }; DOutputData DMotor::Calc(double LiftW) { me = LiftW; mr = 2.0; m = mr + me - (mp/2); k = 0.5 * rho * Cd * A; q = sqrt((T-(m * g))/k); x = ((2 * k * q)/m); t = I / T; v = q * (1 - exp(-x * t)) / (1 + exp(-x * t)); y1 = (-m/(2 * k)) * log(((m * g) + (k * sqr(v))/(T - (m * g)))); m = mr + me - mp; yc = (m/(2 * k)) * log(((m * g) + (k * sqr(v)))/(m * g)); qa = sqrt((m * g) / k); qb = sqrt((g * k) / m); ta = (tan(v / qa)) / (qb); OutD.yc = yc; OutD.y1 = y1; OutD.yt = yc + y1; return OutD; } class DRocket { public: DMotor Engine; double Weight; DRocket() { Weight = 32; } DOutputData OutD; DOutputData Calc(); }; DOutputData DRocket::Calc() { OutD = Engine.Calc(Weight); return OutD; }