remove val= from individual components

Author: xjjiang

aviary/subsystems/geometry/gasp_based/empennage.py

@@ -90,7 +90,7 @@ def setup(self):
                        desc="VBARH | VBARV: Horizontal tail volume coefficient"
                        )
 
-        add_aviary_input(self, Aircraft.Wing.AREA, val=1370)
+        add_aviary_input(self, Aircraft.Wing.AREA)
 
         self.add_input("r_arm", 0.2307, units="unitless",
                        desc=(

aviary/subsystems/geometry/gasp_based/non_dimensional_conversion.py

@@ -14,7 +14,7 @@ def initialize(self):
         add_aviary_option(self, Aircraft.Wing.HAS_STRUT)
 
     def setup(self):
-        add_aviary_input(self, Aircraft.Wing.SPAN, val=0)
+        add_aviary_input(self, Aircraft.Wing.SPAN)
 
         if self.options[Aircraft.Strut.DIMENSIONAL_LOCATION_SPECIFIED]:
             add_aviary_input(self, Aircraft.Strut.ATTACHMENT_LOCATION)
@@ -70,7 +70,7 @@ def initialize(self):
         add_aviary_option(self, Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED)
 
     def setup(self):
-        add_aviary_input(self, Aircraft.Wing.SPAN, val=0)
+        add_aviary_input(self, Aircraft.Wing.SPAN)
 
         if self.options[Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED]:
             add_aviary_input(self, Aircraft.Wing.FOLDED_SPAN)

aviary/subsystems/geometry/gasp_based/wing.py

@@ -548,7 +548,7 @@ def setup(self):
                         desc="SLM_NF: taper ratio between wing root and fold location",
                         )
 
-        add_aviary_output(self, Aircraft.Wing.FOLDING_AREA, val=50)
+        add_aviary_output(self, Aircraft.Wing.FOLDING_AREA)
 
         self.add_output("nonfolded_wing_area", val=150, units="ft**2",
                         desc="SW_NF: wing area of part of wings that does not fold",
@@ -560,7 +560,7 @@ def setup(self):
                         desc="AR_NF: aspect ratio of non-folding part of wing",
                         )
 
-        add_aviary_output(self, Aircraft.Fuel.WING_VOLUME_GEOMETRIC_MAX, val=0)
+        add_aviary_output(self, Aircraft.Fuel.WING_VOLUME_GEOMETRIC_MAX)
 
         self.declare_partials(
             "nonfolded_taper_ratio",