diff --git a/src/FDM/YASim/Airplane.cpp b/src/FDM/YASim/Airplane.cpp
index c5adde2f5..8941ef145 100644
--- a/src/FDM/YASim/Airplane.cpp
+++ b/src/FDM/YASim/Airplane.cpp
@@ -787,35 +787,35 @@ void Airplane::applyDragFactor(float factor)
     float applied = Math::pow(factor, SOLVE_TWEAK);
     _dragFactor *= applied;
     if(_wing)
-      _wing->setDragScale(_wing->getDragScale() * applied);
+      _wing->multiplyDragCoefficient(applied);
     if(_tail)
-      _tail->setDragScale(_tail->getDragScale() * applied);
+      _tail->multiplyDragCoefficient(applied);
     int i;
     for(i=0; i<_vstabs.size(); i++) {
-	Wing* w = (Wing*)_vstabs.get(i);
-	w->setDragScale(w->getDragScale() * applied);
+        Wing* w = (Wing*)_vstabs.get(i);
+        w->multiplyDragCoefficient(applied);
     }
     for(i=0; i<_fuselages.size(); i++) {
-	Fuselage* f = (Fuselage*)_fuselages.get(i);
-	int j;
-	for(j=0; j<f->surfs.size(); j++) {
-	    Surface* s = (Surface*)f->surfs.get(j);
-	    if( isVersionOrNewer( YASIM_VERSION_32 ) ) {
-		// For new YASim, the solver drag factor is only applied to
-		// the X axis for Fuselage Surfaces.
-		// The solver is tuning the coefficient for longitudinal drag,
-		// along the direction of flight. A fuselage's lateral drag
-		// is completely independent and is normally much higher;
-		// it won't be affected by the streamlining done to reduce
-		// longitudinal drag. So the solver should only adjust the
-		// fuselage's longitudinal (X axis) drag coefficient.
-		s->setXDrag(s->getXDrag() * applied);
-	    } else {
-		// Originally YASim applied the drag factor to all axes
-		// for Fuselage Surfaces.
-		s->setDragCoefficient(s->getDragCoefficient() * applied);
-	    }
-	}
+        Fuselage* f = (Fuselage*)_fuselages.get(i);
+        int j;
+        for(j=0; j<f->surfs.size(); j++) {
+            Surface* s = (Surface*)f->surfs.get(j);
+            if( isVersionOrNewer( YASIM_VERSION_32 ) ) {
+            // For new YASim, the solver drag factor is only applied to
+            // the X axis for Fuselage Surfaces.
+            // The solver is tuning the coefficient for longitudinal drag,
+            // along the direction of flight. A fuselage's lateral drag
+            // is completely independent and is normally much higher;
+            // it won't be affected by the streamlining done to reduce
+            // longitudinal drag. So the solver should only adjust the
+            // fuselage's longitudinal (X axis) drag coefficient.
+            s->setXDrag(s->getXDrag() * applied);
+            } else {
+            // Originally YASim applied the drag factor to all axes
+            // for Fuselage Surfaces.
+            s->setDragCoefficient(s->getDragCoefficient() * applied);
+            }
+        }
     }
     for(i=0; i<_weights.size(); i++) {
 	WeightRec* wr = (WeightRec*)_weights.get(i);
diff --git a/src/FDM/YASim/FGFDM.cpp b/src/FDM/YASim/FGFDM.cpp
index bd689d9e2..5bad06e85 100644
--- a/src/FDM/YASim/FGFDM.cpp
+++ b/src/FDM/YASim/FGFDM.cpp
@@ -853,7 +853,7 @@ Wing* FGFDM::parseWing(XMLAttributes* a, const char* type, Version * version)
     w->setInducedDrag(0.7*attrf(a, "idrag", 1));
 
     float effect = attrf(a, "effectiveness", 1);
-    w->setDragScale(w->getDragScale()*effect);
+    w->multiplyDragCoefficient(effect);
 
     _currObj = w;
     return w;
diff --git a/src/FDM/YASim/Wing.cpp b/src/FDM/YASim/Wing.cpp
index 00ef265cb..e4be7666e 100644
--- a/src/FDM/YASim/Wing.cpp
+++ b/src/FDM/YASim/Wing.cpp
@@ -253,7 +253,7 @@ void Wing::addSurface(Surface* s, float weight, float twist)
     _surfs.add(sr);
 }
 
-void Wing::setDragScale(float scale)
+void Wing::setDragCoefficient(float scale)
 {
     _dragScale = scale;
     for(int i=0; i<_surfs.size(); i++) {
@@ -262,6 +262,11 @@ void Wing::setDragScale(float scale)
     }
 }
 
+void Wing::multiplyDragCoefficient(float factor)
+{
+    setDragCoefficient(_dragScale * factor);
+}
+
 void Wing::setLiftRatio(float ratio)
 {
     _liftRatio = ratio;
diff --git a/src/FDM/YASim/Wing.hpp b/src/FDM/YASim/Wing.hpp
index 09d3d8cff..2a0d45868 100644
--- a/src/FDM/YASim/Wing.hpp
+++ b/src/FDM/YASim/Wing.hpp
@@ -90,8 +90,8 @@ public:
 
     // The overall drag coefficient for the wing as a whole.  Units are
     // arbitrary.
-    void setDragScale(float scale);
-    float getDragScale() const { return _dragScale; }
+    void setDragCoefficient(float scale);
+    void multiplyDragCoefficient(float factor);
 
     // The ratio of force along the Z (lift) direction of each wing
     // segment to that along the X (drag) direction.