diff --git a/aviary/docs/user_guide/external_aero.ipynb b/aviary/docs/user_guide/external_aero.ipynb
index 2ab8e7981..40936bd6e 100644
--- a/aviary/docs/user_guide/external_aero.ipynb
+++ b/aviary/docs/user_guide/external_aero.ipynb
@@ -84,6 +84,15 @@
     "        This component doesn't do anything, except set the drag and lift\n",
     "        polars from the file we read in.\n",
     "        \"\"\"\n",
+    "\n",
+    "        # Your component will compute CD and CL for a grid of altitudes, machs, and\n",
+    "        # angles of attack, and return them in a multidimensional array as described \n",
+    "        # in the example text.\n",
+    "\n",
+    "        # Because it would be prohibitive to embed something like a vortex lattice\n",
+    "        # code in this example, we are \"cheating\" here by sending a pre-computed\n",
+    "        # drag polar.\n",
+    "        \n",
     "        outputs['drag_table'] = CD\n",
     "        outputs['lift_table'] = CL\n",
     "        \n",
@@ -156,12 +165,18 @@
     "            the pre-mission part of the Aviary problem. This includes sizing, design,\n",
     "            and other non-mission parameters.\n",
     "        \"\"\"\n",
-    "\n",
-    "        return ExternalAero(altitude=self.altitude, mach=self.mach, angle_of_attack=self.angle_of_attack)\n",
-    "\n",
-    "    def mission_outputs(self):\n",
-    "        return [('drag_table', Aircraft.Design.DRAG_POLAR),\n",
-    "                ('lift_table', Aircraft.Design.LIFT_POLAR)]"
+    "        aero_group = om.Group()\n",
+    "        aero = ExternalAero(altitude=self.altitude, mach=self.mach, angle_of_attack=self.angle_of_attack)\n",
+    "        aero_group.add_subsystem(\n",
+    "            'premission_aero', \n",
+    "            aero,\n",
+    "            promotes_inputs=['*'],\n",
+    "            promotes_outputs=[\n",
+    "                ('drag_table', Aircraft.Design.DRAG_POLAR),\n",
+    "                ('lift_table', Aircraft.Design.LIFT_POLAR)\n",
+    "            ]\n",
+    "        )\n",
+    "        return aero_group"
    ]
   },
   {
@@ -264,7 +279,28 @@
     "prob.add_driver(\"SLSQP\")\n",
     "prob.add_design_variables()\n",
     "prob.add_objective(objective_type=\"mass\", ref=-1e5)\n",
-    "prob.setup()"
+    "prob.setup()\n",
+    "prob.set_initial_guesses()\n",
+    "\n",
+    "prob.run_model()\n"
+   ]
+  },
+  {
+   "cell_type": "code",
+   "execution_count": null,
+   "id": "bc8788ba-9b2b-4b81-8251-32db008d3a60",
+   "metadata": {
+    "tags": [
+     "remove-cell"
+    ]
+   },
+   "outputs": [],
+   "source": [
+    "\n",
+    "# Make sure we succesfully passed the polar\n",
+    "from openmdao.utils.assert_utils import assert_near_equal\n",
+    "om_CD = prob.get_val(Aircraft.Design.DRAG_POLAR)[0, 0, 0]\n",
+    "assert_near_equal(om_CD, CD[0, 0, 0], 1e-6)"
    ]
   }
  ],
@@ -285,7 +321,7 @@
    "name": "python",
    "nbconvert_exporter": "python",
    "pygments_lexer": "ipython3",
-   "version": "3.9.18"
+   "version": "3.12.3"
   },
   "orphan": true
  },