//-----------------------------------------------------------------------------
// TestMatrixAdd_MM
//-----------------------------------------------------------------------------
bool TestMatrixAdd_MM()
{
Matrix A("1,2,3;4,5,6");
Matrix B("1,0,1;0,0,1");
Matrix C;
Add_MM(A,B,C);
Matrix ApB("2,2,4;4,5,7");
return ApproxEqual(C,ApB,TOLERANCE);
}
inline void RocketGeometry::Display()
{
double v = 30;
double t = 273.15 + 20;
double rho = 1.225;
double r = Reynolds(rho, v, ltr, t);
double a = 0.01;
double m = Mach(v, t);
double cf = ViscousDrag(r);
double xcp = Xcp(a);
double cn = Cn(a, r, m);
double ca = Ca(a, r, m, cn);
std::cout << "Rocket Geometry: "
<< "\n\nPlanform Areas"
<< "\n - ApN: " << ApN()
<< "\n - ApB: " << ApB()
<< "\n - ApT: " << ApT()
<< "\n - ApF: " << ApF()
<< "\n - Afe: " << Afe()
<< "\n - Afp: " << Afp()
<< "\n\nStability Derivatives"
<< "\n - CnaN: " << NCnaN()
<< "\n - CnaB: " << NCnaB()
<< "\n - CnaT: " << NCnaT()
<< "\n - CnaF: " << NCnaF()
<< "\n\nNorm Force CP"
<< "\n - NcpN: " << NXcpN()
<< "\n - NcpB: " << NXcpB()
<< "\n - NcpT: " << NXcpT()
<< "\n - NcpF: " << NXcpF()
<< "\n\nLift Force CP"
<< "\n - LcpN: " << LXcpN()
<< "\n - LcpB: " << LXcpB()
<< "\n - LcpT: " << LXcpT()
<< "\n - LcpF: " << LXcpF()
<< "\n\nDrag Force"
<< "\n - DragB: " << DragBody(cf)
<< "\n - DragA: " << DragBase(DragBody(cf))
<< "\n - DragF: " << DragFin(cf)
<< "\n - DragI: " << DragInterference(cf)
<< "\n - DragBA: " << DragAlphaBody(a)
<< "\n - DragFA: " << DragAlphaFin(a)
<< "\n\nResults"
<< "\n - Cn: " << cn
<< "\n - Ca: " << ca
<< "\n - Xcp: " << xcp
<< std::endl;
}
inline void RocketGeometry::Update()
{
Ar = PI * sqr(dn / 2);
Ap = ApB() + ApF() + ApN() + ApT();
StabilityConstants(KCna1, KCna2, KXcpa1, KXcpa2);
}
double LCnaB() { return K * ApB() / Ar; }
