diff --git a/gpkitmodels/GP/aircraft/wing/wing.py b/gpkitmodels/GP/aircraft/wing/wing.py
index b947f802..2e40af70 100644
--- a/gpkitmodels/GP/aircraft/wing/wing.py
+++ b/gpkitmodels/GP/aircraft/wing/wing.py
@@ -2,7 +2,7 @@
 import os
 import numpy as np
 import pandas as pd
-from gpkit import Variable, Model, Vectorize, VectorVariable
+from gpkit import Variable, Model, Vectorize
 from .wing_interior import WingInterior
 from .wing_skin import WingSkin
 from .capspar import CapSpar
@@ -27,10 +27,10 @@ def setup(self, N):
         lam = Variable("\\lambda", 0.5, "-", "wing taper ratio")
         return_cmac = lambda c: 2.0/3.0*(1+c[lam]+c[lam]**2)/(1+c[lam])
         cbarmac = Variable("\\bar{c}_{MAC}", return_cmac, "-", "non-dim MAC")
-        eta = VectorVariable(N, "\\eta", np.linspace(0, 1, N), "-", "(2y/b)")
-        return_c = lambda c: [2.0/(1+c[lam])*(1+(c[lam]-1)*e) for e in c[eta]]
-        cbar = VectorVariable(N, "\\bar{c}", return_c, "-",
-                              "normalized chord at nodes")
+        with Vectorize(N):
+            eta = Variable("\\eta", "-", "(2y/b)")
+            cbar = Variable("\\bar{c}", "-",
+                            "normalized chord at nodes")
         with Vectorize(N-1):
             cbave = Variable("\\bar{c}_{ave}", "-", "non-dim mid section chord")
             cave = Variable("c_{ave}", "ft", "mid section chord")
@@ -106,7 +106,7 @@ def setup(self, N=5, lam=0.5):
         mfac = Variable("m_{fac}", 1.2, "-", "wing weight margin factor")
 
         cb, eta, deta, cbarmac = c_bar(lam, N)
-        subdict = {"\\lambda": lam,
+        subdict = {"\\lambda": lam, "\\eta": eta, "\\bar{c}": cb,
                    "\\bar{c}_{ave}": (cb[1:]+cb[:-1])/2,
                    "d\\eta": deta}