add testing method for wing

gpkitmodels/GP/aircraft/wing/wing.py

@@ -6,11 +6,10 @@
 from .wing_interior import WingInterior
 from .wing_skin import WingSkin
 from .capspar import CapSpar
-from .constant_taper_chord import c_bar
 from gpfit.fit_constraintset import XfoilFit
 
 #pylint: disable=invalid-name, attribute-defined-outside-init, unused-variable
-#pylint: disable=too-many-instance-attributes, too-many-locals
+#pylint: disable=too-many-instance-attributes, too-many-locals, no-member
 
 class Planform(Model):
     "The thing that creates the lift"
@@ -97,15 +96,13 @@ class Wing(Model):
     flight_model = WingAero
     loading = WingLoading
 
-    def setup(self, N=5, lam=0.5):
+    def setup(self, N=5):
 
         self.N = N
 
         W = Variable("W", "lbf", "wing weight")
         mfac = Variable("m_{fac}", 1.2, "-", "wing weight margin factor")
 
-        cb, eta, deta, cbarmac = c_bar(lam, N)
-
         self.planform = Planform(N)
         self.skin = WingSkin(self.planform)
         self.components = [self.skin]

gpkitmodels/GP/aircraft/wing/wing_test.py

@@ -0,0 +1,32 @@
+" wing test "
+from gpkitmodels.GP.aircraft.wing.wing import Wing
+from gpkit import Variable, Model
+
+class FlightState(Model):
+    " state variables "
+    def setup(self):
+
+        V = Variable("V", 50, "m/s", "airspeed")
+        rho = Variable("\\rho", 1.255, "kg/m^3", "air density")
+        mu = Variable("\\mu", 1.5e-5, "N*s/m**2", "air viscosity")
+
+        constraints = [V == V, rho == rho, mu == mu]
+
+        return constraints
+
+def wing_test():
+    " test wing models "
+
+    Wcent = Variable("W_{cent}", 100, "lbf", "center weight")
+
+    W = Wing()
+    W.substitutions[W.topvar("W")] = 50
+    fs = FlightState()
+    perf = W.flight_model(W, fs)
+    loading = W.loading(W, Wcent, W.topvar("W"), fs["V"], perf["C_L"])
+
+    m = Model(perf["C_d"], [W, fs, perf, loading])
+    m.solve("mosek")
+
+if __name__ == "__main__":
+    wing_test()