From: ThorstenB <brehmt@gmail.com>
Date: Thu, 14 Apr 2011 22:15:18 +0000 (+0200)
Subject: Adrian Musceac: #303, YASim solver settings
X-Git-Url: https://git.mxchange.org/?a=commitdiff_plain;h=7f5a0e35184677c21f1eafdfbe6438eb644cdbff;p=flightgear.git

Adrian Musceac: #303, YASim solver settings
The internal solver of YASim which computes drag and lift
coefficients now actually uses the values configured in
the XML input file for approach fuel, cruise fuel and cruise
glide angle.
---

diff --git a/src/FDM/YASim/Airplane.cpp b/src/FDM/YASim/Airplane.cpp
index 483da4269..f63eaaa5e 100644
--- a/src/FDM/YASim/Airplane.cpp
+++ b/src/FDM/YASim/Airplane.cpp
@@ -671,8 +671,8 @@ void Airplane::compile()
         t->handle = body->addMass(0, t->pos);
         totalFuel += t->cap;
     }
-    _cruiseWeight = _emptyWeight + totalFuel*0.5f;
-    _approachWeight = _emptyWeight + totalFuel*0.2f;
+    _cruiseWeight = _emptyWeight + totalFuel*_cruiseFuel;
+    _approachWeight = _emptyWeight + totalFuel*_approachFuel;
 
     body->recalc();
 
@@ -795,7 +795,7 @@ void Airplane::setupWeights(bool isApproach)
 
 void Airplane::runCruise()
 {
-    setupState(_cruiseAoA, _cruiseSpeed,_approachGlideAngle, &_cruiseState);
+    setupState(_cruiseAoA, _cruiseSpeed,_cruiseGlideAngle, &_cruiseState);
     _model.setState(&_cruiseState);
     _model.setAir(_cruiseP, _cruiseT,
                   Atmosphere::calcStdDensity(_cruiseP, _cruiseT));