inline double GetVequivalentFPS(void) const { return veas; }
inline double GetVequivalentKTS(void) const { return veas*fpstokts; }
+ inline double GetTotalTemperature(void) const { return tat; }
+
+ // total pressure above is freestream total pressure for subsonic only
+ // for supersonic it is the 1D total pressure behind a normal shock
+ inline double GetTotalPressure(void) const { return pt; }
+
inline FGColumnVector3& GetPilotAccel(void) { return vPilotAccel; }
inline double GetPilotAccel(int idx) const { return vPilotAccel(idx); }
FGColumnVector3 GetNpilot(void) const { return vPilotAccelN; }
double vcas;
double veas;
double mach;
- double qbar,rhosl,rho,p,psl,pt;
+ double qbar,rhosl,rho,p,psl,pt,tat,sat;
// Don't add a getter for pt!
- // pt above is freestream total pressure for subsonic only
- // for supersonic it is the 1D total pressure behind a normal shock
- // if a general freestream total is needed, e-mail Tony Peden
- // (apeden@earthlink.net) or you can add it your self using the
- // isentropic flow equations
FGColumnVector3 vPilotAccel;
FGColumnVector3 vPilotAccelN;