Merge pull request #631 from danielenriquez59/develop

Using the wrong span variable in Cnr calculation

trunk/SUAVE/Analyses/Stability/Fidelity_Zero.py

@@ -170,7 +170,7 @@ def __call__(self,conditions):
             # Derivative of yawing moment with respect to the rate of yaw
             cDw = aero.drag_breakdown.parasite['main_wing'].parasite_drag_coefficient # Might not be the correct value
             l_v = geometry.wings['vertical_stabilizer'].origin[0][0] + geometry.wings['vertical_stabilizer'].aerodynamic_center[0] - geometry.wings['main_wing'].origin[0][0] - geometry.wings['main_wing'].aerodynamic_center[0]
-            stability.static.Cn_r = Supporting_Functions.cn_r(cDw, geometry.wings['vertical_stabilizer'].areas.reference, Sref, l_v, span, geometry.wings['vertical_stabilizer'].dynamic_pressure_ratio, geometry.wings['vertical_stabilizer'].CL_alpha)
+            stability.static.Cn_r = Supporting_Functions.cn_r(cDw, geometry.wings['vertical_stabilizer'].areas.reference, Sref, l_v, Span, geometry.wings['vertical_stabilizer'].dynamic_pressure_ratio, geometry.wings['vertical_stabilizer'].CL_alpha)
 
             # Derivative of rolling moment with respect to roll rate
             stability.static.Cl_p = Supporting_Functions.cl_p(conditions.lift_curve_slope, geometry)