Updated to match changes in radiostack.[ch]xx

[flightgear.git] / src / FDM / JSBSim / FGPropeller.cpp

diff --git a/src/FDM/JSBSim/FGPropeller.cpp b/src/FDM/JSBSim/FGPropeller.cpp
index 5804117fce13ea9f88f7c1378675ad0b62ee47b6..1bd9118ef6de4cfe8401b8e1d437f923c182d4aa 100644 (file)
--- a/src/FDM/JSBSim/FGPropeller.cpp
+++ b/src/FDM/JSBSim/FGPropeller.cpp
@@ -127,7 +127,7 @@ FGPropeller::~FGPropeller()
 double FGPropeller::Calculate(double PowerAvailable)
 {
   double J, C_Thrust, omega;
-  double Vel = fdmex->GetTranslation()->GetvAeroUVW(eU);
+  double Vel = fdmex->GetTranslation()->GetAeroUVW(eU);
   double rho = fdmex->GetAtmosphere()->GetDensity();
   double RPS = RPM/60.0;
   double alpha, beta;
@@ -154,9 +154,16 @@ double FGPropeller::Calculate(double PowerAvailable)
   }
 
   Thrust = C_Thrust*RPS*RPS*Diameter*Diameter*Diameter*Diameter*rho;
-  vFn(1) = Thrust;
   omega = RPS*2.0*M_PI;
 
+  // Check for windmilling.
+  double radius = Diameter * 0.375; // 75% of radius
+  double windmill_cutoff = tan(Pitch * 1.745329E-2) * omega * radius;
+  if (Vel > windmill_cutoff)
+    Thrust = -Thrust;
+
+  vFn(1) = Thrust;
+
   // The Ixx value and rotation speed given below are for rotation about the
   // natural axis of the engine. The transform takes place in the base class
   // FGForce::GetBodyForces() function.
@@ -170,6 +177,12 @@ double FGPropeller::Calculate(double PowerAvailable)
   ExcessTorque = PowerAvailable / omega;
   RPM = (RPS + ((ExcessTorque / Ixx) / (2.0 * M_PI)) * deltaT) * 60.0;
 
+                               // The friction from the engine should
+                               // stop it somewhere; I chose an
+                               // arbitrary point.
+  if (RPM < 5.0)
+    RPM = 0;
+
   vMn = fdmex->GetRotation()->GetPQR()*vH + vTorque*Sense;
 
   return Thrust; // return thrust in pounds
@@ -183,10 +196,11 @@ double FGPropeller::GetPowerRequired(void)
 
   double cPReq, RPS = RPM / 60.0;
 
-  double J = fdmex->GetTranslation()->GetvAeroUVW(eU) / (Diameter * RPS);
+  double J = fdmex->GetTranslation()->GetAeroUVW(eU) / (Diameter * RPS);
   double rho = fdmex->GetAtmosphere()->GetDensity();
 
   if (MaxPitch == MinPitch) { // Fixed pitch prop
+    Pitch = MinPitch;
     cPReq = cPower->GetValue(J);
   } else {                    // Variable pitch prop
     double advance = fdmex->GetFCS()->GetPropAdvance(ThrusterNumber);