<?xml version="1.0" encoding="UTF-8"?>
<AeolusASP>
    <Info version="4.25" timestamp="03/09/2022 16:40:55"/>
    <Model type="propeller" nblades="2" rpm="-2100.0" adjustment="1.94" name="APC_ThinElectric_19x12_NACA4412">
        <UnitSystem type="si10"/>
        <Wings>
            <Wing name="Blade" color="0.0 0.5450000166893005 0.8199999928474426">
                <Geometry origin="0.0 0.0 0.0" epsilon_ref="0.446" scale="1.0">
                    <Settings chordMode="0"/>
                    <Airfoils>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.036195" l="0.0270256" alpha_wt="-55.89" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.04826" l="0.0304038" alpha_wt="-47.12" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.060325" l="0.0340233" alpha_wt="-49.17" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.07239" l="0.0366776" alpha_wt="-54.95" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.084455" l="0.0381254" alpha_wt="-59.57" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.09652" l="0.038608" alpha_wt="-63.17" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.108585" l="0.0383667" alpha_wt="-66.03" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.12065" l="0.0371602" alpha_wt="-68.36" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.132715" l="0.0354711" alpha_wt="-70.27" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.14478" l="0.0332994" alpha_wt="-72.07" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.156845" l="0.0306451" alpha_wt="-73.74" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.16891" l="0.0275082" alpha_wt="-75.05" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.180975" l="0.0246126" alpha_wt="-76.19" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.19304" l="0.0214757" alpha_wt="-77.02" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.205105" l="0.0185801" alpha_wt="-77.81" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.21717" l="0.0156845" alpha_wt="-78.19" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.229235" l="0.0118237" alpha_wt="-78.75" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                        <Airfoil name="NACA4412" refinement="0.9" refinementSourceTop="0.6" refinementSourceBot="0.6" s="0.2413" l="0.0077216" alpha_wt="-79.34" phi="0.0" dihedral="0.0" inverted="false" flapchord="0.2" flapdeflection="0.0"/>
                    </Airfoils>
                </Geometry>
                <Discretization smooth="false" npwingstrip="52">
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                    <Strip stripdensity="0.4" type="Constant"/>
                </Discretization>
            </Wing>
        </Wings>
        <FlightCondition aircraftWeight="0.0" fluid="air" altitude="0.0" temperature="0.0" trueSpeed="10.0" cdviscwet="0.008"/>
        <Computation symmetry="false" numberOfCores="16" aoa="-3.0 5.0 10.0 " nsubpanels="15" normalizedzetaoffset="0.005" wakelengthfactor="5.0" normalizedfarfield="5.0"/>
        <Optimization enabled="false">
            <GoalType goalType="maximize"/>
            <ObjectiveFunction objective="propeller_thrust"/>
            <Optimizer algorithm="BOBYQA" maxEvaluations="1000"/>
        </Optimization>
        <ParamaterStudies enabled="true" nsteps="10">
            <ObjectiveFunction objective="propeller_efficiency"/>
            <DesignVariables>
                <DesignVariable min="0.0" max="13.5" key="flightcondition truespeed "/>
            </DesignVariables>
        </ParamaterStudies>
    </Model>
</AeolusASP>