<?xml version="1.0" encoding="UTF-8"?>
<AeolusASP>
    <Info version="4.14" timestamp="06/09/2020 20:19:19"/>
    <Model type="aircraft">
        <UnitSystem type="si10"/>
        <Wings>
            <Wing name="Main wing" color="0.0 0.5450000166893005 0.8199999928474426">
                <Geometry origin="0.0 0.0 0.0" epsilon_ref="0.0">
                    <Settings chordMode="0"/>
                    <Airfoils>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.0" l="1.5" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.2" l="1.46" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.3" l="1.44" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.3" flapdeflection="20.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="2.0" l="1.1" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.3" flapdeflection="20.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="2.1" l="1.08" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="2.7" l="0.96" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="2.8" l="0.94" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.3" flapdeflection="-15.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="4.5" l="0.5" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.3" flapdeflection="-15.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="4.6" l="0.47" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.0" l="0.38" alpha_wt="0.0" phi="4.0" dihedral="0.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.05" l="0.368" alpha_wt="0.0" phi="10.0" dihedral="15.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.1" l="0.35" alpha_wt="0.0" phi="15.0" dihedral="30.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.15" l="0.33" alpha_wt="0.0" phi="44.0" dihedral="45.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.2" l="0.225" alpha_wt="1.0" phi="55.0" dihedral="60.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.25" l="0.16" alpha_wt="2.0" phi="55.0" dihedral="75.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.3" l="0.14" alpha_wt="3.0" phi="45.0" dihedral="90.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.4" l="0.14" alpha_wt="4.0" phi="45.0" dihedral="90.0" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA0015" refinement="0.8" refinementSourceTop="0.6" refinementSourceBot="0.6" s="5.6" l="0.08" alpha_wt="1.0" phi="0.0" dihedral="0.0" flapchord="0.2" flapdeflection="0.0"/>
                    </Airfoils>
                </Geometry>
                <Discretization npwingstrip="50">
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                    <Strip stripdensity="0.8" type="Constant"/>
                </Discretization>
            </Wing>
        </Wings>
        <Propulsion>
        </Propulsion>
        <FlightCondition aircraftWeight="2000.0" fluid="air" altitude="2000.0" temperature="15.0" trueSpeed="30.0" cdviscwet="0.005"/>
        <Computation symmetry="true" numberOfCores="4" aoa="-3.0 5.0 10.0 " nsubpanels="15" normalizedzetaoffset="0.005" wakelength="1000.0" normalizedfarfield="5.0"/>
        <Optimization enabled="false">
            <GoalType goalType="maximize"/>
            <ObjectiveFunction objective="currentE"/>
            <Optimizer algorithm="BOBYQA" maxEvaluations="1000"/>
        </Optimization>
        <ParamaterStudies enabled="false" nsteps="20">
            <ObjectiveFunction objective="currentE"/>
        </ParamaterStudies>
    </Model>
</AeolusASP>