YASim: bugfix for wing section (wrong surface positions).

Reformated and extended output of CLI tool.

src/FDM/YASim/Surface.cpp

@@ -63,7 +63,8 @@ void Surface::setOrientation(const float* o)
 {
     for(int i=0; i<9; i++) _orient[i] = o[i];
     if (_surfN) {
-        float xaxis[3] {-1,0,0};
+        // export the chord line (transformed into aircraft coordiantes)
+        float xaxis[3] {1,0,0};
         Math::tmul33(_orient,xaxis, xaxis);
         _surfN->getNode("axis-x", true)->setFloatValue(xaxis[0]);
         _surfN->getNode("axis-y", true)->setFloatValue(xaxis[1]);

src/FDM/YASim/Wing.cpp

@@ -332,10 +332,15 @@ void Wing::compile()
                 nSegs = 8;
             float segWid = ws->_length * (end - start)/nSegs;
 
+            float base[3];
+            _chord2float(ws->_rootChord, base);
+            float tip[3];
+            _chord2float(ws->_tipChord, tip);
+            
             for(int j=0; j<nSegs; j++) {
                 float frac = start + (j+0.5f) * (end-start)/nSegs;
                 float pos[3];
-                interp(_base, _tip, frac, pos);
+                interp(base, tip, frac, pos);
 
                 float chord = ws->_rootChord.length * (1 - (1-ws->_taper)*frac);
                 float weight = chord * segWid;
@@ -518,15 +523,23 @@ void Wing::writeInfoToProptree()
 
     for (int section=0; section < _sections.size(); section++) {
         ws = (WingSection*)_sections.get(section);
+        float mass {0};
         for (int surf=0; surf < ws->numSurfaces(); surf++) {
             Surface* s = ws->getSurface(surf);
             float drag = s->getTotalForceCoefficient();
             dragSum += drag;
 
-            float mass = ws->getSurfaceWeight(surf);
+            mass = ws->getSurfaceWeight(surf);
             mass = mass * Math::sqrt(mass);
             wgt += mass;
         }
+        SGPropertyNode_ptr sectN = _wingN->getChild("section",section,1);
+        sectN->getNode("surface-count", true)->setFloatValue(ws->numSurfaces());
+        sectN->getNode("weight", true)->setFloatValue(mass);
+        sectN->getNode("base-x", true)->setFloatValue(ws->_rootChord.x);
+        sectN->getNode("base-y", true)->setFloatValue(ws->_rootChord.y);
+        sectN->getNode("base-z", true)->setFloatValue(ws->_rootChord.z);
+        sectN->getNode("chord", true)->setFloatValue(ws->_rootChord.length);
     }
     _wingN->getNode("weight", true)->setFloatValue(wgt);
     _wingN->getNode("drag", true)->setFloatValue(dragSum);
@@ -574,4 +587,15 @@ float Wing::updateModel(Model* model)
     return _weight;
 }
 
+void Wing::printSectionInfo()
+{
+    WingSection* ws;
+    printf("#wing sections: %d\n", _sections.size());
+    for (int section=0; section < _sections.size(); section++) {
+        ws = (WingSection*)_sections.get(section);
+        printf("Section %d base point (%.3f, %.3f, %.3f), chord %.3f\n", section,
+               ws->_rootChord.x, ws->_rootChord.y, ws->_rootChord.z, ws->_rootChord.length);
+    }
+}
+
 }; // namespace yasim

src/FDM/YASim/Wing.hpp

@@ -189,6 +189,7 @@ public:
 
     void setPropertyNode(SGPropertyNode_ptr n) { _wingN = n; };
     float updateModel(Model* model);
+    void  printSectionInfo();
 };
 
 }; // namespace yasim

src/FDM/YASim/yasim-test.cpp

@@ -274,21 +274,23 @@ int main(int argc, char** argv)
       printf("soft limit CG-x   : %.3f m\n", a->getCGSoftLimitXMin());
       printf("hard limit CG-x   : %.3f m\n", a->getCGHardLimitXMin());
       printf("\n");
-      printf("        wing span: %.2f m\n", a->getWingSpan());
-      printf(" sweep lead. edge: %.1f .. %.1f deg\n", sweepMin, sweepMax);
-      printf("        wing area: %.2f m²\n", a->getWingArea());
-      printf("  wing load empty: %.2f kg/m² (Empty %.0f kg)\n", a->getWingLoadEmpty(), a->getEmptyWeight());
-      printf("   wing load MTOW: %.2f kg/m² (MTOW  %.0f kg)\n", a->getWingLoadMTOW(), a->getMTOW());
-      printf("\n");
-      printf("        tail span: %.3f m\n", tail->getSpan());
-      printf("        tail area: %.3f m²\n", tail->getArea());
-      printf("\n");
       printf("wing lever        : %.3f m\n", a->getWingLever());
       printf("tail lever        : %.3f m\n", a->getTailLever());
       printf("\n");
       printf("max thrust        : %.2f kN\n", a->getMaxThrust()/1000);
       printf("thrust/empty      : %.2f\n", a->getThrust2WeightEmpty());
       printf("thrust/mtow       : %.2f\n", a->getThrust2WeightMTOW());
+      printf("\n");
+      printf("wing span         : %.2f m\n", a->getWingSpan());
+      printf("sweep lead. edge  : %.1f .. %.1f deg\n", sweepMin, sweepMax);
+      printf("wing area         : %.2f m^2\n", a->getWingArea());
+      printf("wing load empty   : %.2f kg/m^2 (Empty %.0f kg)\n", a->getWingLoadEmpty(), a->getEmptyWeight());
+      printf("wing load MTOW    : %.2f kg/m^2 (MTOW  %.0f kg)\n", a->getWingLoadMTOW(), a->getMTOW());
+      printf("\n");
+      printf("tail span         : %.3f m\n", tail->getSpan());
+      printf("tail area         : %.3f m^2\n", tail->getArea());
+      printf("\n");
+      wing->printSectionInfo();
     }
     printf("\nInertia tensor [kg*m^2], origo at CG:\n\n");
     printf("  %7.0f, %7.0f, %7.0f\n", SI_inertia[0], SI_inertia[1], SI_inertia[2]);